TY - GEN
T1 - Aeroelastic divergence and free vibration of tapered composite wings
AU - Yu, Mengchun
AU - Hwu, Chyanbin
PY - 2007/1/1
Y1 - 2007/1/1
N2 - In aeroelasticity, divergence of wing structures is an important static phenomenon. On the other hand, the free vibration analysis is significant to investigate the dynamic characteristics of the structure. Recently, a comprehensive wing model considering the airfoil shape was established. However, the analysis of tapered wing was still not taken into account so far. In this paper, this model is extended to discuss the tapered composite wings. By employing the Hamilton's principle and following the standard procedure of finite element formulation, an elementwise comprehensive model was developed. Because this model can be applied to both static and dynamic analyses, divergence and free vibration will be studied. In this model, aerodynamic force vector containing the lift and moment of the wings was approximated by the strip theory, which will then lead to a standard eigen-relation for solving the divergence dynamic pressure by neglecting the inertial terms. Besides, this model will also provide another eigen-relation for solving the natural frequencies when all the external forces are eliminated.
AB - In aeroelasticity, divergence of wing structures is an important static phenomenon. On the other hand, the free vibration analysis is significant to investigate the dynamic characteristics of the structure. Recently, a comprehensive wing model considering the airfoil shape was established. However, the analysis of tapered wing was still not taken into account so far. In this paper, this model is extended to discuss the tapered composite wings. By employing the Hamilton's principle and following the standard procedure of finite element formulation, an elementwise comprehensive model was developed. Because this model can be applied to both static and dynamic analyses, divergence and free vibration will be studied. In this model, aerodynamic force vector containing the lift and moment of the wings was approximated by the strip theory, which will then lead to a standard eigen-relation for solving the divergence dynamic pressure by neglecting the inertial terms. Besides, this model will also provide another eigen-relation for solving the natural frequencies when all the external forces are eliminated.
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M3 - Conference contribution
AN - SCOPUS:85076868032
SN - 9784931136052
T3 - ICCM International Conferences on Composite Materials
BT - Proceedings of the 16th International Conference on Composite Materials, ICCM-16 - "A Giant Step Towards Environmental Awareness
PB - International Committee on Composite Materials
ER -