TY - GEN
T1 - Direct-drive electric motor for starc-abl tail-cone propulsor
AU - Yoon, Andy
AU - Arastu, Faraz
AU - Lohan, Danny
AU - Xiao, Jianqiao
AU - Haran, Kiruba
N1 - Funding Information:
The authors would like to acknowledge Andrew Provenza and NASA for supporting this project under SBIR Contract No. 80NSSC18P1898. Thanks to Dr. Jayant Sabnis and Dr. Sheppard Salon for useful discussions related to the technical development of this propulsor concept.
Publisher Copyright:
© 2019 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2019
Y1 - 2019
N2 - A direct-drive, electric motor has been developed to power the tailcone propulsor for the NASA STARC-ABL aircraft. Reduced-order optimization was used to explore three propulsor concepts and converge on a motor topology that meets the STARC-ABL’s power density and efficiency requirements. Subsequent studies using high-fidelity finite-elements analysis were conducted to obtain the final motor rated for 2.6 MW, 11 kW/kg, and 98% efficiency. Reliability concerns related to turbo-electric aircraft have been addressed by introducing a segmented motor powered by parallel inverters to protect against open-circuit faults. The suspension system for the integrated motor and fan has been designed to account for thrust forces experienced during flight and an upstream motor configuration has been designed for assembling the propulsion system onto the fuselage for flight testing.
AB - A direct-drive, electric motor has been developed to power the tailcone propulsor for the NASA STARC-ABL aircraft. Reduced-order optimization was used to explore three propulsor concepts and converge on a motor topology that meets the STARC-ABL’s power density and efficiency requirements. Subsequent studies using high-fidelity finite-elements analysis were conducted to obtain the final motor rated for 2.6 MW, 11 kW/kg, and 98% efficiency. Reliability concerns related to turbo-electric aircraft have been addressed by introducing a segmented motor powered by parallel inverters to protect against open-circuit faults. The suspension system for the integrated motor and fan has been designed to account for thrust forces experienced during flight and an upstream motor configuration has been designed for assembling the propulsion system onto the fuselage for flight testing.
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U2 - 10.2514/6.2019-4516
DO - 10.2514/6.2019-4516
M3 - Conference contribution
AN - SCOPUS:85095967517
SN - 9781624105906
T3 - AIAA Propulsion and Energy Forum and Exposition, 2019
BT - AIAA Propulsion and Energy Forum and Exposition, 2019
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy Forum and Exposition, 2019
Y2 - 19 August 2019 through 22 August 2019
ER -