An improved propeller design method for the electric aircraft

Xiang, Song; Liu, Yuanqiang; Tang, Gang; Zhao, Weigang; Sheng-xi, Tong; Li, Yadong

doi:10.1016/j.ast.2018.05.008

Cited by 23 publications

(8 citation statements)

References 11 publications

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“…The module calculates the thrust at a given throttle position and airspeed, and also estimates the electric power consumption. The model was designed and verified with wind-tunnel testing to match the operational conditions of an electric aircraft from the literature [25]. In the module, the propeller performance is represented as two-dimensional lookup tables that provide thrust and absorbed shaft power values as Some limitations exist in the 'EMA Power Model' module described above.…”

Section: Propulsionmentioning

confidence: 99%

A Generic Mission-Level Flight Control Surface EMA Power Consumption Simulation Tool

Heerden

Judt

et al. 2022

Aerospace

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The use of electromechanical actuators (EMAs) for aeronautical applications promises substantial benefits regarding efficiency and operability. To advance the design of power electronics and secondary power supply, there is a need for the ability to swiftly study the effects of aircraft mission and operational aspects on the actuator energy consumption. Pursuant to this, the aim of the work presented in this paper is twofold: (i) to build a generic mission-level flight control surface EMA power consumption simulation framework and (ii) to apply this framework to a case study involving a small all-electric aircraft, in which selected factors that impact energy consumption are investigated. The core of the framework comprises physics-based EMA power estimators, linked with a six-degree-of-freedom flight dynamics and control simulation module. The case study results show that the actuator power consumption correlates positively with the proportional gains in the flight control system but is inversely proportional to the trajectory radius and linearly dependent on turbulence intensity. The developed framework could aid in the selection of the actuator, as well as in the optimisation of airborne electronics and secondary power supply.

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Section: Propulsionmentioning

confidence: 99%

A Generic Mission-Level Flight Control Surface EMA Power Consumption Simulation Tool

Heerden

Judt

et al. 2022

Aerospace

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“…Flying would therefore also become more environmentally friendly and more quiet [53,54]. Electric power for a two-seat aircraft is discussed in [55]. The more electric aircraft (MEA) concept is discussed in [56].…”

Section: Electric Motors: Environmentally Friendly Flyingmentioning

confidence: 99%

Energy Efficiency Management: State of the Art and Improvement Potential Analysis with Regard to Cargo Transport by Air and Rail

Cermak¹,

Markl²,

Lackner³

2020

Transportation Systems Analysis and Assessment

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This review article summarizes the state of the art in energy efficiency (EE) management in air and rail cargo transportation. After an introduction, explanations and definitions follow around the topic of energy efficiency. The political framework conditions of the European Union (EU) as well as the associated European Union Emissions Trading System are described. In particular, the drive technologies, CO 2 emissions, and fuel-saving options are reviewed.

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“…Experimental propeller tests can be performed with forced [ 11 ] and without forced airflow [ 12 ]. The former allows for performance evaluation during flight (when the relative air velocity is different from zero).…”

Section: Introductionmentioning

confidence: 99%

Wind Tunnel Performance Tests of the Propellers with Different Pitch for the Electric Propulsion System

Czyż

Karpiński

Skiba

et al. 2021

Sensors

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The geometry of a propeller is closely related to its aerodynamic performance. One of the geometric parameters of a propeller is pitch. This parameter determines the distance by which the propeller moves forward during one revolution. The challenge is to select a propeller geometry for electric propulsion in order to achieve the best possible performance. This paper presents the experimental results of the aerodynamic performance of the set of propellers with different pitch values. The tests were performed in a closed-circuit subsonic wind tunnel using a six-component force balance. The analyzed propellers were 12-inch diameter twin-blade propellers that were driven by a BLDC (brushless direct current) electric motor. The tests were performed under forced airflow conditions. The thrust and torque produced by the propeller were measured using a strain gauge. The analysis was performed for different values of the advance ratio which is the ratio of freestream fluid speed to propeller tip speed. Additionally, a set of electrical parameters was recorded using the created measurement system. The propeller performance was evaluated by a dimensional analysis. This method enables calculation of dimensionless coefficients which are useful for comparing performance data for propellers.

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An improved propeller design method for the electric aircraft

Cited by 23 publications

References 11 publications

A Generic Mission-Level Flight Control Surface EMA Power Consumption Simulation Tool

A Generic Mission-Level Flight Control Surface EMA Power Consumption Simulation Tool

Energy Efficiency Management: State of the Art and Improvement Potential Analysis with Regard to Cargo Transport by Air and Rail

Wind Tunnel Performance Tests of the Propellers with Different Pitch for the Electric Propulsion System

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