Abstract
A design outline is given of the actuator that rotates the engine and rotor nacelles on the V-22 aircraft. The actuator comprises a two-stage telescopic ballscrew that is driven either hydraulically from one end or electrically from the other. Requirements for structural redundancy, least weight, operation after any single failure and performance at low temperatures are shown to influence the choice of actuator configuration and the design of assemblies.
Get full access to this article
View all access options for this article.