Abstract
The aim of this paper is to conduct experimental modal analysis and numerical simulation to verify the structural characteristics of a deployable-retractable wing for aircraft and spacecraft. A modal impact test was conducted in order to determine the free vibration characteristics. Natural frequencies and vibration mode shapes were obtained via measurement in LMS Test. Lab. The frequency response functions were identified and computed by force and acceleration signals, and then mode shapes of this morphing wing structure were subsequently identified by PolyMAX modal parameter estimation method. FEM modal analysis was also implemented and its numerical results convincingly presented the mode shape and natural frequency characteristics were in good agreement with those obtained from experimental modal analysis. Experimental study in this paper focuses on the transverse response of morphing wing as its moveable part is deploying or retreating. Vibration response to different rotation speeds have been collected, managed and analyzed through the use of comparison methodology with each other. Evident phenomena have been discovered including the resonance on which most analysis is focused because of its potential use to generate large amplitude vibration of specific frequency or to avoid such resonant frequencies from a wide spectrum of response. Manufactured deployable-retractable wings are studied in stage of experimental modal analysis, in which some nonlinear vibration resulted should be particularly noted because such wing structure displays a low resonant frequency which is always optimal to be avoided for structural safety and stability.
Highlights
In recent years, there has been considerable research focusing on aircraft morphing wing [1] due to its high efficiency during manoeuvre or flight operations
This morphing wing concept can be classified into three major types: planform alternation, out-of-plane transformation, and airfoil adjustment
The PolyMAX method is a mathematical approach related to the least-square complex frequency-domain (LSCF) estimation method
Summary
There has been considerable research focusing on aircraft morphing wing [1] due to its high efficiency during manoeuvre or flight operations. This is because aircrafts with morphing structures are able to change its configuration in order to adapt to varying flight conditions and to maximize its performance. This morphing wing concept can be classified into three major types: planform alternation, out-of-plane transformation, and airfoil adjustment. The wing airfoil cross-sectional profile could be lively adjusted while the wing fixture remains unaltered
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