US 12,009,671 B2
System and method for ground fault monitoring in an aircraft
Frederic Lacaux, Woodinville, WA (US); Shengyi Liu, Sammamish, WA (US); Eugene V. Solodovnik, Kenmore, WA (US); Vyacheslav Khozikov, Bellevue, WA (US); and Kamiar J. Karimi, Kirkland, WA (US)
Assigned to The Boeing Company, Chicago, IL (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Feb. 17, 2022, as Appl. No. 17/674,669.
Prior Publication US 2023/0261476 A1, Aug. 17, 2023
Int. Cl. H02J 4/00 (2006.01); B60L 50/51 (2019.01); H02H 3/16 (2006.01); B64D 45/00 (2006.01)
CPC H02J 4/00 (2013.01) [B60L 50/51 (2019.02); H02H 3/165 (2013.01); B60L 2200/10 (2013.01); B60L 2210/40 (2013.01); B64D 2045/0085 (2013.01); B64D 2221/00 (2013.01); H02J 2310/44 (2020.01)] 20 Claims
OG exemplary drawing
 
1. An electrical system for an aircraft, comprising:
a polyphase AC electric power source electrically connected to a polyphase rotary electric motor via a plurality of AC contactors;
an AC/DC inverter electrically connected to the polyphase rotary electric motor;
a DC power bus electrically connected to the AC/DC inverter;
a plurality of sensors arranged to monitor a plurality of electric currents between the polyphase AC electric power source and the polyphase rotary electric motor;
a first controller arranged to control the AC/DC inverter; and
a second controller arranged to monitor the plurality of sensors and operatively connected to the plurality of AC contactors;
wherein the second controller is operable to:
monitor, via the plurality of sensors, the plurality of electric currents between the polyphase AC electric power source and the polyphase rotary electric motor;
detect a fault based upon the plurality of electric currents; and
deactivate the plurality of AC contactors in response to the fault.