Abstract
In this paper experimental tests are described and discussed which illustrate the feasibility of buckling control in composite structural elements using induced strain actuation in a smart technological manner. Compressive tests on simply supported square composite plates which utilise the shape memory effect for buckling control are shown to exhibit substantially reduced post-buckling deflections when under activated control in comparison to those experienced for the uncontrolled case. The alleviation of the post-buckling deflections is shown to result in reduced non-linear stress levels in the post-buckling range and thus it is intimated that the ultimate failure levels of the composite plates can be improved through the application of shape memory control. The influence of temperature, from ohmic heating of the actuated shape memory alloy wires, on the mechanical performance of the composite laminated plates is discussed and the analysis procedures for the determination of the resulting non-uniform stress profiles in the composite plates are duly outlined. It was found that temperature effects could be significant and that these in turn depended to a large extent on laminate lay-up configuration. Particular attention is paid in the paper to tests carried out to ascertain the characteristic behaviour of the Nickel–Titanium shape memory material employed for actuation purposes. The cyclic recovery force capabilities of the actuator wires utilised in the compressive plate tests is highlighted and a detailed account of the determination of the alloys characteristic transformation temperatures is given. The paper discusses, in some detail, the feasibility of the proposed smart structural concept and gives some thought to the implementation of smart advanced composite materials within the marketplace with particular reference to future aerospace applications.
Published Version
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