The prospects and potential of all electric aircraft

Cronin, Michael J.

doi:10.2514/6.1983-2478

Cited by 5 publications

(2 citation statements)

References 5 publications

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“…These two categories differ from conventional aircrafts as they include electrically driven alternatives to traditional aircraft subsystems [4][5][6]. However, the AEA concept goes as far back as the Second World War, when the US and the UK produced an all-electric military bomber aircraft that had the advantage of simple/clean installation and elimination of oil leakage and oil contamination, hence eradicating the possibility of fire hazards [7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Progress in Redundant Electromechanical Actuators for Aerospace Applications

Annaz,

Kaluarachchi

2023

Aerospace

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The power to move aircraft control surfaces has advanced from being manually generated (by the pilot and transmitted via rods and links) to electrically transmitted (via wires) to operate control surface actuators. Various hydraulic, electromagnetic, and electromechanical architectures have been developed to provide the necessary power and to maintain the expected redundancy. Numerous aircraft actuator system designs have been proposed in the past decades, but a comprehensive review has yet to be undertaken. This review paper aims to fill this gap by providing a critical review of the actuation system designs developed for a variety of aircraft. The review focuses on aircraft actuator system designs, namely: electrohydraulic actuator systems, electromechanical actuator systems, and the force-fighting effect in redundant actuation systems. The significance and operational principle of each actuator system are critically analysed and discussed in the review. The paper also evaluates the solution proposed to address force-fight equalization (or force-fight cancelation) in force or torqued-summed architectures. Future trends in redundant actuation system development with reduced force-fighting effect in aircraft actuator systems are also addressed.

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Section: Introductionmentioning

confidence: 99%

Progress in Redundant Electromechanical Actuators for Aerospace Applications

Annaz,

Kaluarachchi

2023

Aerospace

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“…To prevent the aircraft wings and stabilizers from ice accretion, all commercial aircrafts are equipped with ice protection systems [2]. Generally, the thermal anti-icing system is the most widely used for large commercial aircraft and it also accounts for about 20% energy consumption of the aircraft engines [3][4][5]. Therefore, it is critical to optimize the thermal anti-icing system to achieve energy conservation, which can lighten the take-off weight and extend the flying range [6,7].…”

Section: Introductionmentioning

confidence: 99%

Investigation on the Mechanism of Heat Load Reduction for the Thermal Anti-Icing System

Zhu

Zhang

2020

Energies

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The aircraft ice protection system that can guarantee flight safety consumes a part of the energy of the aircraft, which is necessary to be optimized. A study for the mechanism of the heat load reduction in the thermal anti-icing system under the evaporative mode was presented. Based on the relationship between the anti-icing heat load and the heating power distribution, an optimization method involved in the genetic algorithm was adopted to optimize the anti-icing heat load and obtain the optimal heating power distribution. An experiment carried out in an icing wind tunnel was conducted to validate the optimized results. The mechanism of the anti-icing heat load reduction was revealed by analyzing the influences of the key factors, such as the heating range, the surface temperature and the convective heat transfer coefficient. The results show that the reduction in the anti-icing heat load is actually the decrease in the convective heat load. In the evaporative mode, decreasing the heating range outside the water droplet impinging limit can reduce the convective heat load. Evaporating the runback water in the high-temperature region can lead to the less convective heat load. For the airfoil, the heating power distribution that has an opposite trend with the convective heat transfer coefficient can reduce the convective heat load. Thus, the optimal heating power distribution has such a trend that is low at the leading edge, high at the water droplet impinging limit and zero at the end of the protected area.

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Notes on 'The electric control of large aeroplanes'

Thompson¹

1988

IEEE Aerosp. Electron. Syst. Mag.

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The prospects and potential of all electric aircraft

Cited by 5 publications

References 5 publications

Progress in Redundant Electromechanical Actuators for Aerospace Applications

Progress in Redundant Electromechanical Actuators for Aerospace Applications

Investigation on the Mechanism of Heat Load Reduction for the Thermal Anti-Icing System

Notes on 'The electric control of large aeroplanes'

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