This chapter approaches the vibration of continuous systems using a physical discretization of the system. An early approach to this discretization process employed flexibility influence coefficients, but this was superseded by the Finite Element (FE) method. The Finite Element approach is widely used in aircraft aeroelastic and loads calculations. The chapter considers the application of the FE approach to more complex structural representations, and discusses the 'beam‐like' representation. There are two basic forms of rigid body element that are used in aircraft FE modeling: rigid body element with an infinite constraint and rigid body element with an interpolation constraint. When an aircraft component such as a wing or fuselage is to be represented by a 'beam‐like' model using the FE method, a three‐dimensional beam element, more complete than the two‐dimensional bending version considered earlier in this chapter, needs to be employed.
Vibration of Continuous Systems – Finite Element Approach
2014-12-02
20 pages
Article/Chapter (Book)
Electronic Resource
English
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