Hybrid-electric propulsion architecture and method for dissipating electrical energy in such an architecture
US12391124B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 24, 2020 |
| Grant date | Aug 19, 2025 |
| Priority date | — |
| Expiry date | Nov 24, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T90/14
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A hybrid/electric propulsion architecture for a multi-rotor rotary wing aircraft, including an electricity generator driven by an internal combustion engine, and configured to operate in motor mode, a rectifier configured to convert an alternating current delivered by the electricity generator into direct current, an electrical network including a high voltage direct current (HVDC) bus, electrical energy storage means connected to the electrical network, during electrical energy regeneration on the HVDC bus, depending on the state of charge of the storage means: the storage means are configured to recover electrical energy, the storage means and the rectifier are configured to recover electrical energy, and the electricity generator operating in motor mode is configured to recover electrical energy.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.