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The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Patent No.:

US 11634217 B1

PDFFull Text
Date of Patent:
Apr. 25, 2023

Filed:

Jun. 11, 2021

Short takeoff and landing vehicle with forward swept wings

Applicant:

Kitty Hawk Corporation, Palo Alto, CA (US);

Inventors:

Pranay Sinha, Sunnyvale, CA (US);

Damon Vander Lind, Alameda, CA (US);

Assignee:

Kitty Hawk Corporation, Palo Alto, CA (US);

Attorney:

Van Pelt, Yi & James LLP

Primary Examiner:

Ian Jen

Int. Cl.
CPC ...
B64C 29/00 (2006.01); G05D 1/10 (2006.01); B64C 13/48 (2006.01); B64C 39/12 (2006.01); B64D 27/24 (2006.01); B64D 27/26 (2006.01); B60L 53/00 (2019.01); B60L 50/64 (2019.01); B64C 27/82 (2006.01); B64D 27/02 (2006.01); B64D 31/06 (2006.01);
U.S. Cl.
CPC ...
B64C 29/0033 (2013.01); B60L 50/64 (2019.02); B60L 53/00 (2019.02); B64C 13/48 (2013.01); B64C 27/82 (2013.01); B64C 39/12 (2013.01); B64D 27/02 (2013.01); B64D 27/24 (2013.01); B64D 27/26 (2013.01); B64D 31/06 (2013.01); G05D 1/101 (2013.01); B60L 2200/10 (2013.01); B64C 2027/8209 (2013.01); B64D 2027/026 (2013.01); B64D 2027/264 (2013.01);
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.

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