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.:
Date of Patent:
May. 26, 2026
Filed:
Oct. 16, 2024
Applicant:
Archer Aviation Inc., San Jose, CA (US);
Inventors:
Jonathan Anthony Beno, Bellevue, WA (US);
Benjamin Scott Dyer, Huntsville, AL (US);
Nathan Daniel Storrs, Woodinville, WA (US);
Assignee:
Archer Aviation Inc., San Jose, CA (US);
Primary Examiner:
Int. Cl.
CPC ...
B64C 29/00 (2006.01); B60L 15/06 (2006.01); B60L 15/38 (2006.01); B64C 27/54 (2006.01); B64D 27/30 (2024.01); B64D 33/08 (2006.01); B64D 35/02 (2024.01); F16B 2/06 (2006.01); F16H 57/08 (2006.01); H02K 1/27 (2022.01); H02K 1/32 (2006.01); H02K 5/124 (2006.01); H02K 5/20 (2006.01); H02K 7/08 (2006.01); H02K 7/116 (2006.01); H02K 9/19 (2006.01); H02K 11/33 (2016.01); H02K 15/03 (2025.01); H02M 7/5395 (2006.01); H02P 21/00 (2016.01); H02P 25/16 (2006.01); H02P 27/06 (2006.01); H02P 27/08 (2006.01); H02K 7/00 (2006.01);
U.S. Cl.
CPC ...
B64C 29/0033 (2013.01); B60L 15/06 (2013.01); B60L 15/38 (2013.01); B64C 27/54 (2013.01); B64C 29/0008 (2013.01); B64D 27/30 (2024.01); B64D 33/08 (2013.01); B64D 35/02 (2013.01); F16B 2/06 (2013.01); F16H 57/08 (2013.01); H02K 1/27 (2013.01); H02K 1/32 (2013.01); H02K 5/124 (2013.01); H02K 5/203 (2021.01); H02K 7/08 (2013.01); H02K 7/116 (2013.01); H02K 9/19 (2013.01); H02K 11/33 (2016.01); H02K 15/03 (2013.01); H02M 7/5395 (2013.01); H02P 21/50 (2016.02); H02P 25/16 (2013.01); H02P 27/06 (2013.01); H02P 27/08 (2013.01); B60L 2200/10 (2013.01); B60L 2210/40 (2013.01); H02K 7/006 (2013.01);
Abstract
A tilting apparatus for an aircraft, comprising: a tiltable aircraft component which tilts between a first and second position, at least one actuator for adjusting a tilt angle of the tiltable aircraft component, and at least one passive damper connected to the tiltable aircraft component and configured to limit a rate of change of the tilt angle of the tiltable aircraft component. The at least one passive damper is on a load path separate from a load path of the at least one actuator.