@inproceedings{oai:jaxa.repo.nii.ac.jp:00005661,
 author = {Luber, Wolfgang},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of Lectures and Workshop International: Recent Advances in Multidisciplinary Technology and Modeling},
 month = {Feb},
 note = {As part of the 'Advanced Aircraft Structures Program', feasibility studies of different structural concepts of active and morphing structures have been performed. These studies have revealed significant problems related to system complexity and functionality under environmental conditions and severe problems combined with the development of adequate materials. In the first part, comparison of active smart structure-piezoelectric control systems and aerodynamic active systems for vibration alleviation and elastic mode damping of a military aircraft structure is presented. The vibration alleviation systems which are operative at flight in turbulence or during maneuvers at high incidence reduce severe buffeting levels on the vertical tail structure. The Active Systems for elastic mode Damping (ASD) are designed as digital systems to provide vibration alleviation and have an interface to the Flight Control System (FCS) or are directly part of the FCS. The sensor concept of all different systems is the same as the sensor concept used for the FCS with the corresponding benefits of redundancy and safety. The design of systems and the comparisons of system properties are based on open and closed loop response calculations, performed with the dynamic model of the total aircraft including coupling of flight mechanics, structural dynamics, FCS dynamics and hydraulic actuator or piezo-actuator dynamics. Aerodynamic systems, like active foreplane and flap concepts, rudder and auxiliary rudder concepts, and piezoelectric systems, like piezo interface at the interconnection fin to rear fuselage and integrated piezo concepts are compared. Besides the essential effects on flexible aircraft mode stability and vibration alleviation factors system complexity and safety aspects are described. Recently, aerodynamic investigations of adaptive deformable aircraft structures on a scale model of an actual aircraft have been performed with aerodynamic CFD (Computational Fluid Dynamics) simulations and wind tunnel tests on a complete aircraft model with different shapes of the wing trailing edge. The aerodynamic investigations have shown a considerable drag reduction. Novel concepts are now under investigation, which might lead to a promising way ahead. One of these concepts uses transversal actuators, which are distributed in the aircraft skin. Detailed analyses of this approach have shown the potential and viability of this approach. Especially it could be shown that the expected weight increase of the adaptive wing structure including actuators is lower than the achieved overall weight decrease of the airplane due to the reduced drag., 資料番号: AA0063824006, レポート番号: JAXA-SP-07-008E},
 pages = {52--63},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Component concepts for morphing structures},
 volume = {JAXA-SP-07-008E},
 year = {2008}
}