A three degree-of-freedom aeroelastic typical section with control surface freeplay is modeled theoretically as a system of piecewise linear state-space models . The system response is determined by time marching of the governing equations using a standard Runge -Kutta algorithm in conjunction with
A numerical and experimental study on the nonlinear behavior of laminated composite structural components
β Scribed by Won-Man Cho; Sung-Kie Youn; Young-shin Lee
- Publisher
- Elsevier Science
- Year
- 1995
- Tongue
- English
- Weight
- 508 KB
- Volume
- 57
- Category
- Article
- ISSN
- 0045-7949
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