Aircraft and methods of operating the same to increase descent angles thereof

Patent metadata

Field	Value
Publication number	US-12151808-B2
Application number	US-202217820302-A
Country	US
Kind code	B2
Filing date	Aug 17, 2022
Priority date	Aug 17, 2022
Publication date	Nov 26, 2024
Grant date	Nov 26, 2024

Abstract

Aircraft and methods of operating the aircraft to provide for increased descent angles. The aircraft includes a fuselage having fixed wings, a horizontal thrust source coupled to the fuselage and configured to selectively generate and supply horizontal thrust to the aircraft, a vertical thrust source coupled to the fuselage and configured to selectively generate and supply vertical thrust to the aircraft, the vertical thrust source including a vertical thrust rotor that is configured to selectively operate in a locked mode, in which the vertical thrust rotor cannot rotate freely in response to contact of airflow therewith, and an unlocked mode, in which the vertical thrust rotor can rotate freely in response to contact of airflow therewith, and a controller configured to selectively supply a command to the vertical thrust source that causes the vertical thrust rotor to operate in the unlocked mode.

First claim

What is claimed is:

1. An aircraft comprising:
a fuselage having fixed wings;
a horizontal thrust source coupled to the fuselage and configured to selectively generate and supply horizontal thrust to the aircraft;
a vertical thrust source coupled to the fuselage and configured to selectively generate and supply vertical thrust to the aircraft, the vertical thrust source including a vertical thrust rotor that is configured to selectively operate in a locked mode, in which the vertical thrust rotor cannot rotate freely in response to contact of airflow therewith, and an unlocked mode, in which the vertical thrust rotor can rotate freely in response to contact of airflow therewith; and
a controller in operable communication with at least the vertical thrust source, the controller configured to selectively supply a command to the vertical thrust source that causes the vertical thrust rotor to operate in the unlocked mode.

2. The aircraft of claim 1 , wherein the controller supplies the command to the vertical thrust source during a descent of the aircraft to increase aerodynamic drag of the aircraft through autorotation/windmilling of the vertical thrust rotor and thereby increase a descent angle of the aircraft.

3. The aircraft of claim 1 , wherein the controller is configured to supply the command to the vertical thrust source based on a flight path descent angle and an aircraft descent velocity and a deceleration rate threshold.

4. The aircraft of claim 1 , wherein the controller is configured to, by a processor:
receive a preprogramed flight path descent angle for landing the aircraft;
determine a required drag based on an aircraft descent velocity and a deceleration rate threshold, wherein the required drag is necessary to achieve the preprogramed flight path descent angle; and
supply the command to the vertical thrust source in response to the determined required drag being greater than a current or expected drag of the aircraft,
wherein rotation of the vertical thrust rotor increases the current drag of the aircraft to the determined required drag.

5. The aircraft of claim 4 , wherein the controller is configured to, by a processor:
receive a preprogramed flight path descent angle for landing the aircraft;
determine a maximum safe descent angle based on an aircraft descent velocity and a deceleration rate threshold; and
supply the command to the vertical thrust source in response to the determined maximum safe descent angle being less than the preprogramed flight path descent angle,

wherein rotation of the vertical thrust rotor increases the current drag of the aircraft to the determined required drag.

6. The aircraft of claim 1 , wherein the aircraft is a fixed wing vertical take-off and landing vehicle.

7. The aircraft of claim 1 , wherein the vertical thrust source is a dedicated vertical thrust source.

8. The aircraft of claim 1 , wherein the aircraft is operable in a wing-borne flight mode wherein lift is primarily provided by the fixed wings, and a rotor-borne flight mode wherein lift is primarily provided by the vertical thrust source.

9. A method of operating an aircraft, the method comprising:
operating the aircraft to fly along a preprogrammed flight path by generating horizontal thrust with a horizontal thrust source and generating lift with fixed wings coupled to a fuselage of the aircraft; and
selectively supplying a command to a vertical thrust source coupled to the fuselage that causes a vertical thrust rotor of the vertical thrust source transitions from operating in a locked mode to operating in an unlocked mode,
wherein the vertical thrust rotor cannot rotate freely in response to contact of airflow therewith while operating in the locked mode, and in which the vertical thrust rotor can rotate freely in response to contact of airflow therewith while operating in the unlocked mode.

10. The method of claim 9 , wherein the command is supplied to the vertical thrust source during a descent of the aircraft to increase aerodynamic drag of the aircraft through autorotation/windmilling of the vertical thrust rotor and thereby increase a descent angle of the aircraft.

11. The method of claim 9 , wherein the command is supplied to the vertical thrust source based on a flight path descent angle and an aircraft descent velocity and a deceleration rate threshold.

12. The method of claim 9 , further comprising:
receiving a preprogramed flight path descent angle for landing the aircraft;
determining a required drag based on an aircraft descent velocity and a deceleration rate threshold, wherein the required drag is necessary to achieve the preprogramed flight path descent angle; and
supplying the command to the vertical thrust source in response to the determined required drag being greater than a current or expected drag of the aircraft,
wherein rotation of the vertical thrust rotor increases the current drag of the aircraft to the determined required drag.

13. The method of claim 12 , further comprising:
receiving a preprogramed flight path descent angle for landing the aircraft;
determining a maximum safe descent angle based on an aircraft descent velocity and a deceleration rate threshold; and
supplying the command to the vertical thrust source in response to the determined maximum safe descent angle being less than the preprogramed flight path descent angle,
wherein rotation of the vertical thrust rotor increases the current drag of the aircraft to the determined required drag.

14. The method of claim 9 , wherein the aircraft is a fixed wing vertical take-off and landing vehicle.

15. The method of claim 9 , wherein the vertical thrust source is a dedicated vertical thrust source.

16. The method of claim 9 , wherein operating the aircraft to fly along the preprogrammed flight path includes operating the aircraft in a wing-borne flight mode wherein lift is primarily provided by the fixed wings, the method further comprising operating the aircraft in a rotor-borne flight mode wherein lift is primarily provided by the vertical thrust source.

Assignees

• Honeywell Int Inc

Inventors

• Tonet Fleig Pedro Alexandre
• Karas Ondrej

Classifications

• G05D1/654

  Landing (docking at a base station G05D1/661) · CPC title

• G05D1/485

  Control of rate of change of altitude or depth · CPC title

• B64C27/025

  Rotor drives, in particular for taking off; Combination of autorotation rotors and driven rotors · CPC title

• B64U10/20

  Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) · CPC title

• G05D1/102

  specially adapted for vertical take-off of aircraft · CPC title