Aircraft propulsion system configured to substantially cancel component gyroscopic forces
US11746727B2 · kind B2 · utility
1Cited by
2References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 18, 2022 |
| Grant date | Sep 5, 2023 |
| Priority date | — |
| Expiry date | Nov 18, 2042 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft propulsion system comprises a propulsor, a motor and a reduction gearbox coupled to a prime mover at an input side, and the propulsor at an output side. The reduction gearbox is configured to provide a reduction ratio between the input and output. The reduction gearbox is configured such that the input side rotates in an opposite direction to the output side, and the prime mover, motor, propulsor and reduction gearbox are configured such that gyroscopic forces of the propulsor, motor, prime mover and reduction gearbox generated during aircraft manoeuvres and/or propulsion system failures are substantially cancelled.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.