Redundant, Thin-Wing, High-Pressure, Direct-Drive Valve Actuation System

901796

09/01/1990

Event
Aerospace Technology Conference and Exposition
Authors Abstract
Content
Advanced, thin-wing, military aircraft impose difficult space constraints on the design of flight control actuators, resulting in a trend to higher system pressures. Fault-tolerant electro-hydraulic design, combined with increasing bandwidth dynamic requirements, suggests the use of smart actuation with local, servo-loop closures and decentralized data processing capability for improved control and failure management. A partially flightworthy version of a smart actuation system has been developed for a hypothetical aircraft fast-aileron application. The system presently is in a laboratory test program to demonstrate performance under flight-simulated conditions. High-pressure (8000-psi), direct-drive, parallel servoactuators with multichannel analog control and multiprocessor digital redundancy management are integrated into the actuation system. Important aspects of the design and development process are provided with emphasis on the redundancy management system.
Meta TagsDetails
DOI
https://doi.org/10.4271/901796
Pages
18
Citation
Boyer, K., "Redundant, Thin-Wing, High-Pressure, Direct-Drive Valve Actuation System," SAE Technical Paper 901796, 1990, https://doi.org/10.4271/901796.
Additional Details
Publisher
Published
Sep 1, 1990
Product Code
901796
Content Type
Technical Paper
Language
English