Abstract
A structured tailoring and adaptive materials technology for controlling the dynamic response of aircraft wing structures is discussed. The wing structure was modeled as the doubly-tapered composite thin-walled beam including various non-classical features. The influence of patch location and size of piezoactuators upon the control efficiency of the structure span is investigated. The numerical results depicted the application of tailoring and optimal control upon the vibration response of nonuniform wing structures subjected to external pressure pulses.
| Original language | English |
|---|---|
| Pages (from-to) | 217-227 |
| Number of pages | 11 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 2 |
| DOIs | |
| Publication status | Published - 2000 |
| Externally published | Yes |
| Event | 41st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and ExhibitAIAA/ASME/AHS Adaptive Structures ForumAIAA Non-Deterministic Approaches ForumAIAA Space Inflatables Forum - Atlanta, GA, USA Duration: 2000 Apr 3 → 2000 Apr 6 |
ASJC Scopus subject areas
- Architecture
- General Materials Science
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering