Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials
US8733690B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 23, 2010 |
| Grant date | May 27, 2014 |
| Priority date | — |
| Expiry date | Apr 23, 2030 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C29/0033
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.