US 11,952,139 B2
Voltage controlled aircraft electric propulsion system
Peter Schenk, Greenwood, IN (US); David Loder, Indianapolis, IN (US); and David Trawick, Indianapolis, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on May 14, 2021, as Appl. No. 17/321,146.
Prior Publication US 2022/0363402 A1, Nov. 17, 2022
Int. Cl. B64D 31/06 (2006.01); B60L 50/60 (2019.01); B60L 58/19 (2019.01); B64D 27/24 (2006.01); H02J 1/00 (2006.01)
CPC B64D 31/06 (2013.01) [B60L 50/60 (2019.02); B60L 58/19 (2019.02); B64D 27/24 (2013.01); B60L 2200/10 (2013.01); B60L 2210/10 (2013.01); B64D 2221/00 (2013.01); H02J 1/00 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A method of operating an aircraft electric propulsion system comprising:
energizing a power supply bus with a generator power source, a stored energy power source or a combination thereof;
supplying power from the power supply bus to an electric propulsor of an aircraft;
controlling, with a controller circuitry, a voltage magnitude on the power supply bus to a first predetermined voltage;
monitoring an altitude of the aircraft, the altitude being a measured dynamic value indicative of a distance of the aircraft above sea level;
monitoring, with the controller circuitry, an output thrust of the electric propulsor;
controlling, with the controller circuitry, the voltage magnitude on the power supply bus according to the altitude of the aircraft by dynamically adjusting a weighting applied to a set point of the voltage magnitude according to the output thrust of the electric propulsor; and
decreasing the voltage magnitude as the aircraft increases in altitude.