US 11,939,075 B2
Systems and methods for power distribution in a drone aircraft
Hannan Parvizian, San Francisco, CA (US); Manuel Lopez, Richmond, CA (US); and Guangyuan Zheng, San Francisco, CA (US)
Assigned to Sierra Nevada Corporation, Sparks, NV (US)
Filed by Sierra Nevada Corporation, Sparks, NV (US)
Filed on May 10, 2021, as Appl. No. 17/316,601.
Application 17/316,601 is a division of application No. 16/447,860, filed on Jun. 20, 2019, granted, now 11,001,388.
Claims priority of provisional application 62/687,249, filed on Jun. 20, 2018.
Prior Publication US 2021/0261265 A1, Aug. 26, 2021
Int. Cl. B64D 31/06 (2006.01); B64C 29/00 (2006.01); B64C 27/26 (2006.01); B64U 30/10 (2023.01); B64U 30/20 (2023.01); B64U 50/11 (2023.01); B64U 50/19 (2023.01); B64U 50/34 (2023.01); B64U 70/80 (2023.01)
CPC B64D 31/06 (2013.01) [B64C 29/0025 (2013.01); B64C 27/26 (2013.01); B64U 30/10 (2023.01); B64U 30/20 (2023.01); B64U 50/11 (2023.01); B64U 50/19 (2023.01); B64U 50/34 (2023.01); B64U 70/80 (2023.01)] 5 Claims
OG exemplary drawing
 
1. A power distribution system for a drone aircraft, comprising:
at least one electric battery electrically connected to a power management unit installed on a drone aircraft;
an electric propulsion system that produces vertical thrust, electrically connected to the at least one electric battery, wherein the drone aircraft performs Vertical Take-Off and Landing (VTOL) under power of the electric propulsion system;
an internal combustion propulsion system, separate from the electric propulsion system, configured to produce forward thrust independent of the electric propulsion system; and
an electric generator mechanically coupled to the internal combustion propulsion system and electrically connected to the power management unit through a mechanical switch configured to selectively disconnect the power management unit from the electric generator;
wherein, in VTOL flight, the mechanical switch is actuated into an open position, isolating the electric generator and the internal combustion propulsion system from the power management unit and at least one electric battery;
a first voltage regulator electrically connected to a first electric power supply and configured to draw power from the first electric power supply;
a second voltage regulator electrically connected to a second electric power supply and configured to draw power from the second electric power supply;
a power selection unit electrically connected to the first voltage regulator and the second voltage regulator, and configured to draw power from the first voltage regulator; and
a first set of electronic devices electrically connected to the power selection unit and configured to draw power from the power selection unit,
wherein the power selection unit is configured to draw power from the second voltage regulator in response to detecting a failure condition of the first voltage regulator.