公开(公告)号：US11952139B2

公开(公告)日：2024-04-09

申请号：US17321146

申请日：2021-05-14

Applicant: Rolls-Royce Corporation

Inventor： Peter Schenk ,  David Loder ,  David Trawick

IPC: B64D31/06 ,  B60L50/60 ,  B60L58/19 ,  B64D27/24 ,  H02J1/00

CPC classification number: B64D31/06 ,  B60L50/60 ,  B60L58/19 ,  B64D27/24 ,  B60L2200/10 ,  B60L2210/10 ,  B64D2221/00 ,  H02J1/00

Abstract: A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.

公开(公告)号：US20220363402A1

公开(公告)日：2022-11-17

申请号：US17321146

申请日：2021-05-14

Applicant: Rolls-Royce Corporation

Inventor： Peter Schenk ,  David Loder ,  David Trawick

IPC: B64D31/06 ,  B64D27/24 ,  B60L50/60 ,  B60L58/19

Abstract: A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.