Hybrid aircraft and landing launch/recovery system
US11697508B2 · kind B2 · utility
0Cited by
2References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 17, 2020 |
| Grant date | Jul 11, 2023 |
| Priority date | — |
| Expiry date | Dec 24, 2041 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64U2101/31
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A hybrid aircraft system uses a combination of direct propeller driven gas engine and electric motor power to provide vertical thrust and control for hover of the aircraft. Furthermore, a portable launch/recovery system is configured for use with an aircraft such as a Vertical Takeoff and Landing (VTOL) Unmanned Air Vehicle (UAV). The system is configured to enable ships with limited available deck space to become UAV-compatible.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.