Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method
This paper presents an investigation on flutter speed of cracked composite plates. This work is divided into two sections: (a) variation of crack length at a fixed location on the plate, and (b) variation of crack location on the plate with a fixed crack length, modelled as a unidirectional compos...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English English |
| Published: |
Elsevier
2018
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/7/73583%20Aeroelastic%20assessment%20of%20cracked%20composite.pdf http://irep.iium.edu.my/73583/8/73583%20Aeroelastic%20assessment%20of%20cracked%20composite%20SCOPUS.pdf |
| Summary: | This paper presents an investigation on flutter speed of cracked composite plates. This work is divided into two
sections: (a) variation of crack length at a fixed location on the plate, and (b) variation of crack location on the
plate with a fixed crack length, modelled as a unidirectional composite for 00,900 and 1350 orientations. Mori-
Tanaka homogenization model is applied to obtain the effective composite constitutive properties as the function
of fiber and matrix volume fraction. Doublet Lattice Method (DLM) is used to calculate the unsteady aerodynamic
forces, i.e., lift distributions. It is found that the existence of small crack ratio on the composite plate
(less than 0.4) has triggered an increment of the flutter speed. To support this statement, flutter response modes
for each crack ratio are plotted, where the structure appears to be more stiffened than the undamaged plate.
However, the crack results in the reduction of flutter speed when the crack ratio reaches 0.5. For the crack
location assessment, the flutter speed increases as the crack location moves from the root to the tip due to the
reduction of flutter frequency. The results show a good agreement with the validation using Strip Theory considering unsteady aerodynamics. |
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