US 11,685,533 B2
Selectively deployable heated propulsor system
Kyle B. Clark, Underhill, VT (US); Riley Griffin, Montpelier, VT (US); Augustus Brightman, Williston, VT (US); Steven Arms, Shelburne, VT (US); and Herman Wiegman, Essex Junction, VT (US)
Assigned to BETA AIR, LLC, South Burlington, VT (US)
Filed by BETA AIR, LLC, South Burlington, VT (US)
Filed on Aug. 17, 2021, as Appl. No. 17/404,886.
Application 17/404,886 is a continuation of application No. 16/427,298, filed on May 30, 2019, granted, now 11,124,304.
Claims priority of provisional application 62/678,612, filed on May 31, 2018.
Prior Publication US 2021/0380261 A1, Dec. 9, 2021
Int. Cl. B64D 15/02 (2006.01); B64C 29/00 (2006.01); H02K 1/22 (2006.01)
CPC B64D 15/02 (2013.01) [B64C 29/0016 (2013.01); H02K 1/22 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A selectively deployable propulsor system for an electric aircraft, the system comprising:
at least a propulsor mounted on at least a structural feature of the electric aircraft, wherein the at least a propulsor includes:
at least a rotor; and
at least a motor mechanically coupled to the at least a rotor configured to cause the rotor to rotate when activated;
at least a heated chamber configured to comprise the at least a propulsor, wherein the at least a heated chamber and the at least a propulsor are configured to move relative to one another between a first configuration in which the at least a rotor is stowed within the at least a heated chamber and a second configuration in which the at least a rotor is deployed outside of the at least a heated chamber;
at least a temperature sensor configured to detect a temperature of the at least a propulsor; and
at least a vehicle controller coupled to the electric aircraft and the at least a temperature sensor, wherein the at least a vehicle controller is configured to control the movement of the at least a propulsor between the first configuration and the second configuration as a function of the temperature of the at least a propulsor.