In-flight stabilization of an aircraft

Patent metadata

Field	Value
Publication number	US-11584541-B2
Application number	US-202017113647-A
Country	US
Kind code	B2
Filing date	Dec 7, 2020
Priority date	Oct 9, 2019
Publication date	Feb 21, 2023
Grant date	Feb 21, 2023

Abstract

A system for in-flight stabilization including a plurality of flight components mechanically coupled to an aircraft, wherein the plurality of flight components includes a first flight component and a second flight component opposing the first flight component. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure event of a first flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of the first flight component from the sensor, initiate an automatic response as a function of the failure datum. Initiating the automatic response further includes determining an autorotation inducement action for the second flight component to perform and commanding the second flight component to perform the autorotation inducement action.

First claim

What is claimed is:

1. A system for in-flight stabilization, the system comprising:
a plurality of flight components mechanically coupled to an aircraft, wherein the plurality of flight components includes a first flight component and a second flight component opposing the first flight component, wherein the first flight component includes a propulsor;
a sensor mechanically coupled to the aircraft, wherein the sensor includes a torque sensor and is configured to:
detect a failure event of the first flight component; and
generate a failure datum associated to the first flight component, wherein the failure datum includes a determination of torque generation by the propulsor of the first flight component;

a vehicle controller communicatively connected to the sensor, wherein the vehicle controller is configured to:
receive, from the sensor, the failure datum associated to the first flight component; and
initiate an automatic response as a function of the failure datum, the automatic response including:
determining an autorotation inducement action for the second flight component to perform;
commanding the second flight component to perform the autorotation inducement action; and
initiating thrust of a flight component mounted behind a power source of the aircraft.

2. The system of claim 1 , wherein the aircraft further comprises an electric aircraft.

3. The system of claim 1 , wherein each flight component of the plurality of flight components includes a propulsor.

4. The system of claim 1 , wherein the vehicle controller is further communicatively coupled to the plurality of flight components.

5. The system of claim 1 , wherein determining the autorotation inducement action for the second flight component further comprises shutting off the second flight component.

6. The system of claim 1 , wherein determining the autorotation inducement action for the second flight component further comprises:
inducing a reversible rotation for the second flight component.

7. The system of claim 1 , wherein the sensor is further configured to:
detect a failure event of a third flight component of the plurality of flight components; and
generate a failure datum associated to the third flight component.

8. The system of claim 7 , wherein the vehicle controller is further configured to:
receive the failure datum associated to the third flight component; and
initiate the automatic response as a function of the failure datum, the automatic response including:
determining an autorotation inducement action for a fourth flight component of the plurality of flight components to perform, wherein the fourth flight component opposes the third flight component; and
commanding the fourth flight component to perform the autorotation inducement action.

9. The system of claim 8 , wherein determining the autorotation inducement action for the fourth flight component further comprises:
inducing a reversible rotation for the fourth flight component.

10. A method for in-flight stabilization, the method comprising:
detecting, by a sensor, a failure event of a first flight component of a plurality of flight components, wherein the first flight component includes a propulsor;
generating, by the sensor, a failure datum associated to the first flight component, wherein the failure datum includes a determination of torque generation by the propulsor of the first flight component;
receiving, by a vehicle controller, the failure datum associated to the first flight component from the sensor; and
initiating, by the vehicle controller, an automatic response as a function of the failure datum, initiating the automatic response comprising:
determining an autorotation inducement action for the second flight component to perform;
commanding the second flight component to perform the autorotation inducement action; and
initiating thrust of a flight component mounted behind a power source of the aircraft.

11. The method of claim 10 , wherein the aircraft further comprises an electric aircraft.

12. The method of claim 10 , wherein each flight component of the plurality of flight components includes a propulsor.

13. The method of claim 10 , wherein the vehicle controller is communicatively coupled to the plurality of flight components.

14. The method of claim 10 , wherein determining the autorotation inducement action for the second flight component further comprises shutting off the second flight component.

15. The method of claim 10 , wherein determining the autorotation inducement action for the second flight component further comprises:
inducing a reversible rotation for the second flight component.

16. The method of claim 10 , the method further comprising:
detecting, by the sensor, a failure event of a third flight component of the plurality of flight components; and
generating, by the sensor, a failure datum associated to the third flight component.

17. The method of claim 16 , the method further comprising:
receiving, by the vehicle controller, the failure datum associated to the third flight component; and
initiating, by the vehicle controller, the automatic response as a function of the failure datum, the automatic response including:
determining an autorotation inducement action for a fourth flight component of the plurality of flight components to perform, wherein the fourth flight component opposes the third flight component; and
commanding the fourth flight component to perform the autorotation inducement action.

18. The method of claim 17 , wherein determining the autorotation inducement action for the fourth flight component further comprises:
inducing a reversible rotation for the fourth flight component.

Assignees

• Beta Air Llc

Inventors

• List Alexander Hoekje
• Ferrier Lochie

Classifications

• B64D31/06

  actuated automatically · CPC title

• B64D27/34

  All-electric aircraft · CPC title

• B64D31/16

  for electric power plants · CPC title

• B64D45/00 Primary

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C29/0025 Primary

  the propellers being fixed relative to the fuselage · CPC title