Selectively deployable heated propulsor system
AssigneeBeta Air, LLC
InventorsKyle B. Clark, Riley Griffin, Augustus Brightman, Steven Arms, Herman Wiegman
Life of this patent
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Abstract
A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.
Claims20
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.
A method for selectively deploying a propulsor system for an electric aircraft, the method comprising:
- detecting, at an at least a control circuit, at least a change in flight condition;
- receiving, at an at least a vehicle controller, the at least a change in flight condition;
- detecting, by at least a temperature sensor, a temperature of the at least a propulsor;
- and
- controlling, by the at least a vehicle controller, the movement of at least a propulsor of the electric aircraft from a first configuration to a second configuration as a function of the at least a change in flight condition and the temperature of the at least a propulsor, wherein the first configuration is within a heated chamber.
A vehicle with a stowable propulsion system, the vehicle comprising:
- at least a structural feature;
- at least a propulsor mounted on the at least a structural feature, wherein the at least a propulsor includes:
- at least a rotor;
- and
- at least a motor mechanically coupled to the at least a rotor to cause the rotor to rotate when activated;
- at least a heated chamber at the at least a propulsor, wherein the at least a heated chamber and the at least a propulsor, are movable 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 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.
Dependencies are inferred from the claim text.