US 12,214,874 B2
Aerial vehicle
Gad Shaanan, La Jolla, CA (US)
Assigned to Unmanned Aerospace LLC, La Jolla, CA (US)
Filed by Unmanned Aerospace LLC, La Jolla, CA (US)
Filed on Jan. 12, 2024, as Appl. No. 18/411,845.
Application 18/411,845 is a continuation of application No. 18/303,498, filed on Apr. 19, 2023, granted, now 11,873,087.
Application 18/303,498 is a continuation of application No. 17/662,217, filed on May 5, 2022, granted, now 11,661,182, issued on May 30, 2023.
Application 17/662,217 is a continuation of application No. 17/461,719, filed on Aug. 30, 2021, granted, now 11,332,242, issued on May 17, 2022.
Application 17/461,719 is a continuation in part of application No. PCT/US2020/046240, filed on Aug. 13, 2020.
Claims priority of provisional application 63/018,848, filed on May 1, 2020.
Claims priority of provisional application 62/896,257, filed on Sep. 5, 2019.
Claims priority of provisional application 62/886,578, filed on Aug. 14, 2019.
Prior Publication US 2024/0391585 A1, Nov. 28, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. B64C 29/00 (2006.01); B64C 27/02 (2006.01); B64C 27/32 (2006.01); B64C 27/57 (2006.01); B64C 27/59 (2006.01); B64C 27/625 (2006.01); B64C 27/64 (2006.01); B64C 27/82 (2006.01); B64D 27/24 (2006.01); B64D 31/00 (2006.01); B64D 35/02 (2006.01); G05D 1/00 (2006.01); G05D 1/46 (2024.01)
CPC B64C 29/0033 (2013.01) [B64C 27/02 (2013.01); B64C 27/025 (2013.01); B64C 27/32 (2013.01); B64C 27/57 (2013.01); B64C 27/59 (2013.01); B64C 27/625 (2013.01); B64C 27/64 (2013.01); B64C 27/82 (2013.01); B64D 27/24 (2013.01); B64D 31/00 (2013.01); B64D 35/02 (2013.01); B64C 2027/8236 (2013.01); G05D 1/102 (2013.01); G05D 1/46 (2024.01)] 20 Claims
OG exemplary drawing
 
1. A rotor assembly for an aircraft, the rotor assembly comprising:
a central section; and
a blade pitch adjustment linkage comprising:
two mounting members disposed on opposite sides of the central section, each mounting member configured to couple to a rotor blade; and
two gas springs each configured to couple one of the mounting members to the central section and to cause an increase in blade pitch of the rotor blades when subjected to an increased centrifugal force associated with an increase in rotational velocity of the rotor blades, the blade pitch adjustment linkage being configured to maintain the rotor blades at a first blade pitch while a rotational velocity of the rotor blades is slower than a first rotational velocity threshold and to maintain the rotor blades at a second blade pitch while the rotational velocity of the rotor blades is faster than a second rotational velocity threshold greater than the first rotational velocity threshold.