US 12,006,048 B2
Electric power system architecture and fault tolerant VTOL aircraft using same
JoeBen Bevirt, Santa Cruz, CA (US); Alex Stoll, Santa Cruz, CA (US); Martin van der Geest, Santa Cruz, CA (US); Scott MacAfee, Santa Cruz, CA (US); and Jason Ryan, Santa Cruz, CA (US)
Assigned to Joby Aero, Inc., Santa Cruz, CA (US)
Filed by Joby Aero, Inc., Santa Cruz, CA (US)
Filed on Jul. 19, 2021, as Appl. No. 17/379,464.
Application 17/379,464 is a continuation in part of application No. 16/428,794, filed on May 31, 2019, granted, now 11,827,347.
Claims priority of provisional application 63/135,387, filed on Jan. 8, 2021.
Claims priority of provisional application 63/118,504, filed on Nov. 25, 2020.
Claims priority of provisional application 62/678,275, filed on May 31, 2018.
Prior Publication US 2021/0339881 A1, Nov. 4, 2021
This patent is subject to a terminal disclaimer.
Int. Cl. B64D 27/24 (2006.01); B60L 58/22 (2019.01); B64C 29/00 (2006.01)
CPC B64D 27/24 (2013.01) [B60L 58/22 (2019.02); B60L 2200/10 (2013.01); B64C 29/0033 (2013.01); B64D 2221/00 (2013.01)] 21 Claims
OG exemplary drawing
 
1. An electric aircraft comprising:
a battery pair comprising a first and second battery;
a first propulsion assembly comprising:
a dual-wound electric motor comprising a first and second set of windings connected to the first and second batteries, respectively; and
a propeller coupled to the dual-wound electric motor;
a pair of control surfaces arranged on a first side of the mid-sagittal plane of the aircraft, the pair comprising a first and a second control surface; and
a first and a second flight actuator electrically connected to the first and second batteries, respectively, wherein the first and second flight actuators are mechanically connected to the first and second control surfaces, respectively.