2018
DOI: 10.3390/aerospace5030095
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Natural Frequencies of Rectangular Laminated Plates—Introduction to Optimal Design in Aeroelastic Problems

Abstract: Free vibration (or eigenvalue analysis) is a prerequisite for aeroelastic analysis. For divergence analysis, slope influence coefficients (rotation at point i due to unit load at point j) are calculated using free vibration mode shapes and corresponding frequencies. The lowest eigenvalue is of interest and gives the divergence speed. The present paper considers the maximization problem of eigenfrequencies for composite panels. The influence of boundary conditions and constant or variable stiffnesses on optimiz… Show more

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Cited by 20 publications
(7 citation statements)
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“…Fatigue problems of structures with a singular notch [47,48], 4. Free vibrations and flutter problems of plates and cylindrical shells [49][50][51].…”
Section: Analysis Of Macroscopic (Global) Failure Modes Of Composite Structuresmentioning
confidence: 99%
“…Fatigue problems of structures with a singular notch [47,48], 4. Free vibrations and flutter problems of plates and cylindrical shells [49][50][51].…”
Section: Analysis Of Macroscopic (Global) Failure Modes Of Composite Structuresmentioning
confidence: 99%
“…It is possible to reduce the total number of design variables by introducing the pairs of discrete fiber orientations {0 0 2 , ±45 0 , 90 0 2 }-each of the plies has an identical thickness t/N. [57]. However, they are not independent and can be expressed by four natural values: N 0 -the number of pair of plies oriented at 0 0 , N 90 -the number of pair of plies oriented at 90 0 and:…”
Section: Composite Materialsmentioning
confidence: 99%
“…The current work employed a process known as "tailoring the structural design" in order to achieve a specific value for a required parameter-in this case, the system FNFthrough making changes to the structural design in a way that does not adversely affect the structural performance. This process has been utilized in numerous other works in various fields: for example, Chan et al [42] employed the process to change the natural frequency of a wing by changing the angles of its ribs with respect to a range of sweep angles; Tsiatas and Charalampakis [43] employed it to change the natural frequency of axially functionally graded beams and arches by changing their material distribution; and Muc [44] employed the process by changing the ply angles of a laminated plate, among others.…”
Section: Introductionmentioning
confidence: 99%