Selectively deployable heated propulsor system

Patent metadata

Field	Value
Publication number	US-11685533-B2
Application number	US-202117404886-A
Country	US
Kind code	B2
Filing date	Aug 17, 2021
Priority date	May 31, 2018
Publication date	Jun 27, 2023
Grant date	Jun 27, 2023

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.

First claim

What is claimed is:

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.

2. The system of claim 1 , wherein the at least a motor includes at least an electric motor.

3. The system of claim 1 , wherein the at least a propulsor further comprises a retraction mechanism that retracts the at least a rotor into the at least a chamber to place the at least a rotor and the at least a chamber in the first configuration, and extends the rotor out of the at least a chamber to place the at least a rotor and the at least a chamber in the second configuration.

4. The system of claim 1 , wherein the at least a chamber further comprises at least an enclosing panel, and wherein the at least an enclosing panel is configured to enclose the interior space of the at least a chamber in a closed position and relocate forming an opened position exposing the interior space of the at least a chamber.

5. The system of claim 4 , wherein the at least an enclosing panel is configured to retain the at least a rotor in the interior space of the at least a chamber in the first configuration and expose the at least a chamber and at least a rotor in the second configuration.

6. The system of claim 1 , wherein the at least a rotor is further configured to comprise at least a rotor cover configured to couple to the at least a rotor, wherein the at least a rotor cover comprises an aerodynamic exterior surface and a plurality of cavities configured to shelter the at least a rotor and interact with the at least a structural feature when the at least a rotor is in the first configuration.

7. The system of claim 1 , wherein the electric aircraft is an electric vertical takeoff and landing aircraft.

8. The system of claim 1 , wherein the at least a chamber further comprises at least a drainage opening, the at least a drainage opening configured to permit liquid to drain from the at least a chamber.

9. The system of claim 1 further comprising at least a control circuit.

10. The system of claim 9 , wherein the control circuit is further configured to detect at least a change in flight condition.

11. 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.

12. The method of claim 11 , wherein the electric aircraft is an electric vertical takeoff and landing aircraft.

13. The method of claim 11 , wherein the at least a change in flight condition includes a determination that the electric aircraft is entering a cruise phase of flight.

14. The method of claim 11 , wherein the method further comprises:
detecting, at the at least a control circuit, at least a second change in flight condition;
receiving, at the at least a vehicle controller, the at least a second change in flight condition; and
controlling, by the at least a vehicle controller, the movement of the at least propulsor of the electric aircraft from a second configuration to a first configuration as a function of the at least a second change in flight condition.

15. The method of claim 14 , wherein the at least a second change in flight condition includes a determination that the electric aircraft is entering a hover phase of flight.

16. 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.

17. The vehicle of claim 16 , wherein the vehicle further comprises at least a control circuit, wherein the at least a control circuit is configured to detect at least a change in flight condition.

18. The vehicle of claim 17 , wherein the vehicle further comprises an aircraft.

19. The vehicle of claim 18 , wherein the aircraft further comprises an electric aircraft.

20. The vehicle of claim 18 , wherein the aircraft further comprises a vertical takeoff and landing aircraft.

Assignees

• Beta Air Llc

Inventors

• Clark Kyle B
• Griffin Riley
• Brightman Augustus
• Arms Steven
• Wiegman Herman

Classifications

• B64D27/31

  within, or attached to, wings · CPC title

• B64D15/02 Primary

  by ducted hot gas or liquid · CPC title

• B64C29/0025 Primary

  the propellers being fixed relative to the fuselage · CPC title

• B64C29/0016

  the lift during taking-off being created by free or ducted propellers or by blowers · CPC title

• H02K1/22

  Rotating parts of the magnetic circuit · CPC title