US 11,834,167 B2
Hybrid fixed VTOL aircraft powered by heavy fuel engine
Mikhail Blinkov, Hayward, CA (US); Curtis Leo, Los Gatos, CA (US); and Stephen Morris, Sunnyvale, CA (US)
Assigned to Sierra Nevada Corporation, Sparks, NV (US)
Filed by Sierra Nevada Corporation, Sparks, NV (US)
Filed on Apr. 30, 2021, as Appl. No. 17/245,982.
Claims priority of provisional application 63/018,387, filed on Apr. 30, 2020.
Prior Publication US 2021/0339853 A1, Nov. 4, 2021
Int. Cl. B64C 29/00 (2006.01); B64D 31/06 (2006.01); B64D 27/24 (2006.01); B64U 10/20 (2023.01); B64U 30/20 (2023.01); B64U 50/11 (2023.01); B64U 50/13 (2023.01); B64U 50/19 (2023.01); B64D 27/02 (2006.01)
CPC B64C 29/0025 (2013.01) [B64D 27/24 (2013.01); B64D 31/06 (2013.01); B64U 10/20 (2023.01); B64D 2027/026 (2013.01); B64U 30/20 (2023.01); B64U 50/11 (2023.01); B64U 50/13 (2023.01); B64U 50/19 (2023.01)] 18 Claims
OG exemplary drawing
 
1. A Vertical Take-Off and Landing (“VTOL”) drone aircraft, comprising:
a rechargeable battery configured to deliver electrical power to the VTOL drone aircraft;
a primary processor powered by the rechargeable battery, wherein the primary processor directs overall operations of the VTOL drone aircraft;
a plurality of lift propellers in communication with the primary processor and powered by the rechargeable battery, wherein the plurality of lift propellers provides vertical lift for the VTOL drone aircraft;
an internal combustion engine in communication with the primary processor, wherein the internal combustion engine includes a thrust propeller that provides horizontal thrust for the VTOL drone aircraft;
a generator configured to receive power from the internal combustion engine and deliver electrical power to the rechargeable battery to recharge the rechargeable battery;
a power regulation controller in communication with the primary processor, the rechargeable battery, the internal combustion engine, and the generator, wherein the power regulation controller is configured to regulate dynamically power delivery from the internal combustion engine to the thrust propeller and the generator, and from the generator to the rechargeable battery based upon changing conditions during flight of the VTOL drone aircraft; and
a clutch coupled to the thrust propeller, wherein the power regulation controller is in communication with the clutch and is configured to disengage the clutch by a variable amount to limit the delivery of power to the thrust propeller when the internal combustion engine is active.