Selectively deployable heated propulsor system

Patent metadata

Field	Value
Publication number	US-11124304-B2
Application number	US-201916427298-A
Country	US
Kind code	B2
Filing date	May 30, 2019
Priority date	May 31, 2018
Publication date	Sep 21, 2021
Grant date	Sep 21, 2021

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 heated propulsor system, the system comprising:
at least a propulsor mounted on 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 configured to cause the rotor to rotate when activated;

at least a chamber configured to comprise the at least a propulsor, wherein the at least a 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 chamber and a second configuration in which the at least a rotor is deployed outside of the at least a chamber; and
at least a heating element thermally connected to the at least a chamber, wherein the heating element is configured to heat the at least a chamber and at least a rotor when the at least a chamber and the at least a propulsor are in the first configuration.

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 at least a heating element generates heat configured to be retained within the interior space of the at least a chamber when the at least a chamber is in the first configuration.

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 , wherein the heating element further comprises at least a resistive heating element.

10. The system of claim 1 , wherein the heating element heats the at least a chamber and the at least a propulsor using waste heat from at least a vehicular component.

11. The system of claim 1 , wherein the heating element further comprises at least a waste heat conduit.

12. The system of claim 1 further comprising at least a temperature sensor configured to detect a temperature of at least one of the at least a chamber and the at least a propulsor.

13. The system of claim 12 further comprising at least a control circuit electrically coupled to the at least a temperature sensor, the at least a control circuit configured to compare the temperature to a target value and modify a heat output of the at least a heating element.

14. The system of claim 1 further comprising at least an inductive heater, the at least an inductive heater configured to heat the at least a rotor.

15. 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 chamber at the at least a propulsor, wherein the at least a 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 chamber and a second configuration in which the at least a rotor is deployed outside of the at least a chamber; and
at least a heating element thermally connected to the at least a chamber, wherein the heating element heats the chamber and at least a rotor when the at least a chamber and the at least a propulsor are in the first configuration.

16. The vehicle of claim 15 , wherein the vehicle further comprises an aircraft.

17. The vehicle of claim 16 , wherein the aircraft further comprises an electric aircraft.

18. The vehicle of claim 16 , wherein the aircraft further comprises a vertical takeoff and landing aircraft.

Assignees

• Beta Air Llc

Inventors

• Clark Kyle B
• Rothblatt Martine
• 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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D15/12

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title