US 12,246,847 B2
Systems and methods for implementing lightweight and reliable hybrid or electric powertrains for aircraft
Waleed Said, Rockford, IL (US); Rajib Datta, Niskayuna, NY (US); Matt Feddersen, Arlington Heights, IL (US); and Shashank Natesh, Agonquin, IL (US)
Assigned to Zunum Aero, Inc., Redmond, WA (US)
Filed by Zunum Aero, Inc., Bothell, WA (US)
Filed on Mar. 14, 2022, as Appl. No. 17/694,523.
Application 17/694,523 is a continuation of application No. 16/717,902, filed on Dec. 17, 2019, granted, now 11,312,503.
Claims priority of provisional application 62/780,660, filed on Dec. 17, 2018.
Prior Publication US 2023/0023335 A1, Jan. 26, 2023
Int. Cl. B64D 35/02 (2024.01); B64D 41/00 (2006.01)
CPC B64D 35/02 (2013.01) [B64D 41/00 (2013.01); B64D 2221/00 (2013.01)] 43 Claims
OG exemplary drawing
 
1. A hybrid system onboard an aircraft for controlling distribution of power from a multiplicity of energy sources delivering power to one of more direct current (DC) loads, the hybrid system comprising:
an alternating current (AC) generated electrical energy source;
a (high-voltage direct current) HVDC stored electrical energy source;
a rectifier configured to convert AC power from the AC generated electrical energy source to provide a DC power output;
a controller configured to adjust a voltage of the DC power output from the rectifier responsive, at least in part, to a computed voltage setpoint value;
a HVDC bus, and a plurality of electrical switches arranged to switchably couple the HVDC stored electrical energy source and the rectifier to the HVDC bus, wherein the HVDC bus is to receive power from the AC generated electrical energy source or the HVDC stored electrical energy source, or a combination thereof, based, at least in part, on the voltage of the DC power output from the rectifier; and one or more DC loads coupled to receive DC power from the HVDC bus, wherein:
the plurality of switches are configurable to be in a first switching configuration; and the controller is further capable of controlling an operation of the hybrid system, the controller to:
determine a resulting power for the AC generated electrical energy source and the HVDC stored electrical energy source based, at least in part, on a signal indicative of a particular input received in a command from the aircraft and one or more signals indicative of one or more additional inputs received are sample values expressing measured parameters of the AC generated electrical energy source and the HVDC stored electrical energy source; and
utilize the determined resulting power as feedback to determine a proportion of electrical power to be delivered from between the AC generated electrical energy source and the HVDC stored electrical energy source based, at least in part, on a correction to be applied to the particular input.