Brushless direct current (BLDC) motor based linear or rotary actuator for helicopter rotor control
US8915710B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 9, 2005 |
| Grant date | Dec 23, 2014 |
| Priority date | — |
| Expiry date | Nov 7, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/30
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A device for controlling the pitch of a helicopter's rotor blade, the device having a BLDC motor based actuator; and at least one control surface operatively connected to the BLDC motor based actuator. The actuator and the control surface are preferably fully integrated into the interior profile of the rotor blade and are capable of controlling the PFC of the helicopter and improving HHC during operation by reducing noise and vibration. The motor is preferably a high power density motor incorporating rare earth permanent magnets connected to a roller/ball screw or planetary gear set to provide the right combination of force/torque, stroke and frequency.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.