Short takeoff and landing vehicle with forward swept wings

Patent metadata

Field	Value
Publication number	US-11634217-B2
Application number	US-202117345493-A
Country	US
Kind code	B2
Filing date	Jun 11, 2021
Priority date	Oct 9, 2019
Publication date	Apr 25, 2023
Grant date	Apr 25, 2023

Abstract

A vehicle includes a tilt rotor that is aft of a wing and that is attached to the wing via a pylon. The tilt rotor has an adjustable maximum downward angle from horizontal that is less than or equal to 60° and that is set via a setting associated with a flight computer. The vehicle takes off and lands using at least some lift from the wing and from the tilt rotor. In response to a change to the adjustable maximum downward angle, via the setting associated with the flight computer, which produces a new maximum downward angle: the flight computer updates an actuator authority database associated with the flight computer to reflect the new maximum downward angle. Using the updated actuator authority database that reflects the new maximum downward angle, the flight computer generates a rotor control signal for the tilt rotor.

First claim

What is claimed is:

1. A vehicle, comprising:
a tilt rotor that is aft of a wing and that is attached to the wing via a pylon, wherein:
the tilt rotor has an adjustable maximum downward angle from horizontal that is less than or equal to 60°;
the adjustable maximum downward angle is set via a setting associated with a flight computer; and
the vehicle takes off and lands using at least an amount of lift from the wing and at least an amount of lift from the tilt rotor; and

the flight computer configured to instruct the tilt rotor to produce a new maximum downward angle in response to a change to the adjustable maximum downward angle via the setting associated with the flight computer, including by:
updating an actuator authority database associated with the flight computer to reflect the new maximum downward angle; and
generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the new maximum downward angle.

2. The vehicle recited in claim 1 , wherein the wing includes a forward-swept and tapered wing.

3. The vehicle recited in claim 1 , wherein the tilt rotor includes a plurality of hard stops corresponding to different maximum downward angles.

4. The vehicle recited in claim 1 , wherein the tilt rotor is capable of rotating between a cruise position and the adjustable maximum downward angle.

5. The vehicle recited in claim 1 , wherein the new maximum downward angle is determined based at least in part on a length of a runway.

6. The vehicle recited in claim 1 , wherein the new maximum downward angle is determined based at least in part on a desired range for the vehicle.

7. The vehicle recited in claim 1 , wherein in response to the change to the adjustable maximum downward angle, the flight computer further updates a set of permitted flight modes associated with the flight computer to reflect the new maximum downward angle.

8. The vehicle recited in claim 1 , wherein:
the new maximum downward angle is at 90°; and
in response to the change to the adjustable maximum downward angle, the flight computer updates a set of permitted flight modes associated with the flight computer to include a hover flight mode.

9. A method, comprising:
providing a tilt rotor that is aft of a wing and that is attached to the wing via a pylon, wherein:
the tilt rotor is included in a vehicle;
the tilt rotor has an adjustable maximum downward angle from horizontal that is less than or equal to 60°;
the adjustable maximum downward angle is set via a setting associated with a flight computer; and
the vehicle takes off and lands using at least an amount of lift from the wing and at least an amount of lift from the tilt rotor; and

providing the flight computer, wherein the flight computer is configured to instruct the tilt rotor to produce a new maximum downward angle in response to a change to the adjustable maximum downward angle via the setting associated with the flight computer, including by:
updating an actuator authority database associated with the flight computer to reflect the new maximum downward angle; and
generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the new maximum downward angle.

10. The method recited in claim 9 , wherein the wing includes a forward-swept and tapered wing.

11. The method recited in claim 9 , wherein the tilt rotor includes a plurality of hard stops corresponding to different maximum downward angles.

12. The method recited in claim 9 , wherein the tilt rotor is capable of rotating between a cruise position and the adjustable maximum downward angle.

13. The method recited in claim 9 , wherein the new maximum downward angle is determined based at least in part on a length of a runway.

14. The method recited in claim 9 , wherein the new maximum downward angle is determined based at least in part on a desired range for the vehicle.

15. The method recited in claim 9 , wherein in response to the change to the adjustable maximum downward angle, the flight computer further updates a set of permitted flight modes associated with the flight computer to reflect the new maximum downward angle.

16. The method recited in claim 9 , wherein:
the new maximum downward angle is at 90°; and
in response to the change to the adjustable maximum downward angle, the flight computer updates a set of permitted flight modes associated with the flight computer to include a hover flight mode.

Assignees

• Kitty Hawk Corp

Inventors

• Sinha Pranay
• Vander Lind Damon

Classifications

• B64D27/357

  using batteries · CPC title

• B64C27/26

  characterised by provision of fixed wings · CPC title

• B64C29/00

  Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft (rotorcraft B64C27/00) · CPC title

• B64D27/33 Primary

  Hybrid electric aircraft · CPC title

• B64D27/34

  All-electric aircraft · CPC title