	US 12,330,778 B2
	High-speed, vertical take-off and landing aircraft
Joseph John Andrews, Oakland, CA (US)
Appl. No. 17/780,739
Filed by Kymatics, LLC, Pleasanton, CA (US)
PCT Filed Dec. 8, 2020, PCT No. PCT/US2020/063697 § 371(c)(1), (2) Date May 27, 2022, PCT Pub. No. WO2021/201927, PCT Pub. Date Oct. 7, 2021.
Claims priority of provisional application 62/969,151, filed on Feb. 3, 2020.
Claims priority of provisional application 62/946,435, filed on Dec. 11, 2019.
Prior Publication US 2022/0355923 A1, Nov. 10, 2022
Int. Cl. B64C 29/00 (2006.01); B64C 19/00 (2006.01); B64C 27/72 (2006.01); B64D 27/24 (2006.01); B64D 27/40 (2024.01); B64D 35/04 (2006.01); B64D 35/08 (2006.01); B64D 41/00 (2006.01)

CPC B64C 29/0008 (2013.01) [B64C 19/00 (2013.01); B64C 27/72 (2013.01); B64D 27/24 (2013.01); B64D 27/40 (2024.01); B64D 35/04 (2013.01); B64D 35/08 (2013.01); B64D 41/00 (2013.01); B64C 2027/7205 (2013.01)]

20 Claims

1. An aircraft comprising:

a) a lifting structure;

b) a first rotor comprising:

i) a first blade; and

ii) a second blade;

c) a second rotor comprising:

i) a first blade; and

ii) a second blade;

d) an auxiliary propulsion unit; and

e) a control system adapted to independently control an attack angle of each of said blades, wherein:

f) said first rotor:

i) is operable to be rotated about a first mast to provide lift during a first flight mode; and

ii) is operable to be held at a constant first azimuth angle during a second flight mode;

g) said second rotor:

i) is operable to be rotated about a second mast to provide lift during said first flight mode; and

ii) is operable to be held at a constant second azimuth angle during said second flight mode;

h) said auxiliary propulsion unit is operable to provide forward thrust during said second flight mode;

i) to provide control to said aircraft during said second flight mode, said control system is operable to:

i) vary an attack angle of said first blade of said first rotor by a roll control angle; and

ii) vary said attack angle of said first blade of said second rotor by about-a negative of said roll control angle; and

j) to provide pitch control to said aircraft during said second flight mode, said control system is operable to:

i) vary said attack angle of said second blade of said first rotor by a pitch control angle; and

ii) vary said attack angle of said second blade of said second rotor by about said pitch control angle.