Next Article in Journal
The Miniature Optical Communication Transceiver—A Compact, Power-Efficient Lasercom System for Deep Space Nanosatellites
Previous Article in Journal
Practical Approach for Absolute Density Field Measurement Using Background-Oriented Schlieren
Previous Article in Special Issue
Exploitation of a Multifunctional Twistable Wing Trailing-Edge for Performance Improvement of a Turboprop 90-Seats Regional Aircraft
Article Menu
Issue 1 (January) cover image

Export Article

Open AccessArticle
Aerospace 2019, 6(1), 1; https://doi.org/10.3390/aerospace6010001

Electro-Actuation System Strategy for a Morphing Flap

1
Department of Industrial Engineering (Aerospace Division), University of Naples “Federico II”, Via Claudio, 21, 80125 Napoli (NA), Italy
2
Adaptive Structures Division, CIRA—Centro Italiano Ricerche Aerospaziali, 81043 Capua, Italy
*
Authors to whom correspondence should be addressed.
Received: 5 November 2018 / Revised: 17 December 2018 / Accepted: 20 December 2018 / Published: 28 December 2018
Full-Text   |   PDF [10684 KB, uploaded 28 December 2018]   |  

Abstract

Within the framework of the Clean Sky-JTI (Joint Technology Initiative) project, the design and technological demonstration of a novel wing flap architecture were addressed. Research activities were carried out to substantiate the feasibility of morphing concepts enabling flap camber variation in compliance with the demanding safety requirements applicable to the next generation green regional aircraft. The driving motivation for the investigation on such a technology was found in the opportunity to replace a conventional double slotted flap with a single slotted camber-morphing flap assuring similar high lift performances—in terms of maximum attainable lift coefficient and stall angle—while lowering emitted noise and system complexity. The actuation and control logics aimed at preserving prescribed geometries of the device under variable load conditions are numerically and experimentally investigated with reference to an ‘iron-bird’ demonstrator. The actuation concept is based on load-bearing actuators acting on morphing ribs, directly and individually. The adopted un-shafted distributed electromechanical system arrangement uses brushless actuators, each rated for the torque of a single adaptive rib of the morphing structure. An encoder-based distributed sensor system generates the information for appropriate control-loop and, at the same time, monitors possible failures in the actuation mechanism. Further activities were then discussed in order to increase the TRL (Technology Readiness Level) of the validated architecture. View Full-Text
Keywords: actuation; morphing; wing flap; smart system; ground tests; static test; bench test actuation; morphing; wing flap; smart system; ground tests; static test; bench test
Figures

Graphical abstract

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0).
SciFeed

Share & Cite This Article

MDPI and ACS Style

Arena, M.; Amoroso, F.; Pecora, R.; Ameduri, S. Electro-Actuation System Strategy for a Morphing Flap. Aerospace 2019, 6, 1.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Aerospace EISSN 2226-4310 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top