Showing papers by "Rhys Jones published in 2011"
TL;DR: In this paper, a preliminary experimental study and an analysis of the potential application of supersonic particle deposition (SPD) for repairing and restoring the airworthiness and functionality of aging aircraft structures were presented.
53 citations
TL;DR: In this article, the authors examined short crack growth in two quite different materials, viz: 7050-T7451 aluminium alloy and a head hardened rail steel, and found that cracking crack growth conforms to the Generalised Frost-Dugdale model.
19 citations
TL;DR: In this paper, a modified Evolutionary Structural Optimization (ESO) algorithm for optimal design of topologies for complex structures is presented, where a new approach for adaptively controlling the material elimination and a "gauss point average stress" is used as the ESO criterion in order to reduce the generation of checkerboard patterns in the resultant optimal topologies.
Abstract: The paper demonstrates the application of a modified Evolutionary Structural Optimisation (ESO) algorithm for optimal design of topologies for complex structures. A new approach for adaptively controlling the material elimination and a ‘gauss point average stress’ is used as the ESO criterion in order to reduce the generation of checkerboard patterns in the resultant optimal topologies. Also, a convergence criterion is used to examine the uniformity of strength throughout a structure. The ESO algorithm is validated by comparing the ESO based solution with the result obtained using another numerical optimisation method (SIMP).
15 citations
TL;DR: In this paper, the authors examined the crack length versus cycles histories associated with a range of materials, viz: Mil Annealed Ti-6Al-4V, a high strength aerospace steel, several aerospace quality aluminium alloys and several rail wheel steels, subjected to constant amplitude loading.
14 citations
TL;DR: In this article, the application of a modified Evolutionary Structural Optimization (ESO) algorithm for optimal design of topology for an aerospace component is demonstrated. And the capabilities of ESO for producing an optimal design against a specified strength constraint are illustrated using an aerospace design problem of optimisation of the topology of a bulkhead used in an aircraft structure.
13 citations
TL;DR: In this article, the authors presented application of damage tolerance optimisation principles to the design of industrial components using a heuristic optimisation method known as the "Biological algorithm" to determine the shape of the cutout that will maximise its residual strength under the operating loading conditions.
Abstract: The paper presents application of damage tolerance optimisation principles to the design of industrial components. It is illustrated via design optimisation of a Fuel Flow Vent Hole (FFVH) located in the Wing Pivot Fitting (WPF) of an F-111 aircraft. The aim is to determine the shape of the cutout that will maximise its residual strength under the operating loading conditions. Damage tolerance shape optimisation is performed using a heuristic optimisation method known as the ‘Biological algorithm’. The maximum stress intensity factor (SIF) for all of the cracks around the boundary of the optimal cutout is found to be significantly lower compared to that of the initial shape. This shows that an improved residual (fracture) strength is achieved for the optimal designs. The variability in SIF around the cutout boundary is reduced, thereby making the shape more evenly fracture critical. The shapes of the residual strength optimal vent holes are found to depend on the initial crack sizes. It is also shown that a damage tolerance optimisation additionally produces a lighter WPF component design, which is highly desirable for aerospace industries.