Rotor aircraft tilting hub with reduced drag rotor head and mast
US7510377B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 16, 2005 |
| Grant date | Mar 31, 2009 |
| Priority date | — |
| Expiry date | Mar 13, 2027 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C39/04
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A rotor aircraft has a tilting hub for cyclic control operated by either a tilting spindle or swash plate mounted to the upper end of the drive shaft. A spinner housing with two separate half portions encloses the hub. The blades of the rotor have root portions that are integrally joined to the separate half portions. During a collective pitch change, the half portions rotate relative to each other, but at advance ratios greater than about 0.7, when the collective can be held constant, the spinner half portions can be in perfect alignment. Concentric control sleeves surround the drive shaft for changing collective pitch as well as cyclic pitch.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.