Sentence examples for progression in skin-stringer from inspiring English sources

The applied compressive load is increased and induces a progression in skin-stringer separation.

A thorough qualitative discussion concerning the damage initiation and subsequent progression path at the skin-stringer joint is supported by the development of a simple analytical model based on the Classical Laminate Theory denominated as 3-spot-joint 3-spot-joint 3-spot-joint

These numerical analyses aimed to study in detail the onset and propagation of damage in the skin-stringer joint during the load procedure.

The objective of this paper is to investigate the within-the-bond guided wave propagation in a composite skin-stringer joint.

Finally, a parametric analysis has been carried out in order to study the influence of the geometrical parameters of single stiffened composite panels in terms of skin-stringer debonding including Fibre Bridging.

It was found that the amplitude and directivity patterns of scattered fields are affected by the presence of damage, such that SHM design guidelines can be derived for efficient damage detection in the composite skin-stringer bonded joints.

As a result, a degree of redundancy is inherently built-in to the design process of skin-stringer configurations to mitigate against premature and in-service failure.

A number of numerical examples of stiffened panels with various boundary conditions and five-bay skin-stringer structure, in addition to stiffened plates, have been presented.

Focusing our attention on aircraft related structures, the aim of this paper is to show the application of numerical methodologies to evaluate the behaviour of integrally machined skin-stringer panels in the presence of propagating cracks.

In this paper, a numerical investigation on the inter-laminar and intra-laminar damage mechanisms, characterising the skin-stringer debonding growth in stiffened composite panels subjected to compressive load, has been carried out.

Finally, the developed design methodology has been used to design the skin-stringer panels of one complete bay in the wing-box of a DLR-F6 aircraft.