elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Contact | Deutsch
Fontsize: [-] Text [+]

Overview of Adaptronics in Aeronautical Applications

Breitbach, E. and Anhalt, C. and Monner, H.P. (2001) Overview of Adaptronics in Aeronautical Applications. In: Book of Abstracts, Aeronautics Days 2001, "Preparing for the Global Challenges", p. 207. Aeronautics Days 2001, Hamburg, 29.-31.01.2001.

Full text not available from this repository.

Abstract

The Institute of Structural Mechanics (ISM) at the German Aerospace Center is working on several aeronautical projects dealing with adaptive structures. These structures are characterized by their mul-tifunctionality, i.e. adaptronic actuator systems are structurally integrated such that they serve not only as actuators but also as loadcarrying members of the structure itself. With respect to the fail-safe prin-ciple prevalent in aircraft design, this implies that the actuator elements ought to be operated parallel to passive load-carrying structural elements, allowing not only a sensible distribution of opera-tionally induced loads on active and passive structural elements, but sufficient residual strength after a failure of the actuation function as well. Some examples will be presented at the workshop. In transonic civil transport airplanes the structural and aerodynamic efficiency of cruise flight can be increased significantly by varying the wing camber with a flexible trailing edge and building up a variable bump at the upper surface of the wing, both optimized for every flight condition during the complete mission. In order to provide an optimal gap size between wing and flap during high lift flight with flaps extended, these are actively re-deformed in spanwise direction due to the applied airload which leads to a much better high lift behavior. In high performance aircraft one example is concerned with vibrations of the vertical stabilizer due to vortexes, generated by the wings leading edge. They are reduced by means of an active interface, made of piezoceramic stack actuators, thus resulting in reduced structural loading. Present helicopter research mainly focuses on the improvement of the aerodynamic efficiency and on the reduction of vibrations and acoustic emission. The adaptive blade twist concept, developed by ISM, allows to directly control the twist of the helicopter blades by smart adaptive elements and through this to positively influence the main rotor area which is the primary source for helicopter noise and vibrations.

Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2001,
Title:Overview of Adaptronics in Aeronautical Applications
Authors:
AuthorsInstitution or Email of Authors
Breitbach, E.UNSPECIFIED
Anhalt, C.UNSPECIFIED
Monner, H.P.UNSPECIFIED
Date:2001
Journal or Publication Title:Book of Abstracts, Aeronautics Days 2001, "Preparing for the Global Challenges"
Page Range:p. 207
Editors:
EditorsEmail
European Commission, UNSPECIFIED
Status:Published
Event Title:Aeronautics Days 2001, Hamburg, 29.-31.01.2001
Organizer:European Commission
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L ST - Starrflüglertechnologien
DLR - Research theme (Project):UNSPECIFIED
Location: Braunschweig
Institutes and Institutions:Institute of Composite Structures and Adaptive Systems > Institut für Strukturmechanik
Deposited By: Sibylle Wolff
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 16:04

Repository Staff Only: item control page

Browse
Search
Help & Contact
Informationen
electronic library is running on EPrints 3.3.12
Copyright © 2008-2012 German Aerospace Center (DLR). All rights reserved.