CPC B64D 15/02 (2013.01) [B64C 29/0016 (2013.01); H02K 1/22 (2013.01)] | 20 Claims |
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.
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