ST Engineering Ltd is an integrated engineering group in the aerospace, electronics, military contracting and marine sectors. Headquartered in Singapore, the group reported revenues of $5.05b in FY2007. With a market capitalisation of about $10b, it ranks among the largest companies listed on the Singapore Exchange. ST Engineering has more than 18,000 employees worldwide, and over 100 subsidiaries and associated companies in 21 countries and 35 cities. Wikipedia.
Teng S.,Nanyang Technological University |
Li Q.,Singapore Technologies Engineering |
Liu Y.,Nanyang Technological University
Magazine of Concrete Research | Year: 2014
A micromechanical model is developed to describe the stress-strain behaviours of concrete under uniaxial compression. Two kinds of defects are considered, namely microcracks around the mortar-coarse aggregate interface or the interfacial transition zone and aligned coalesced cracks in the concrete. The mortar-coarse aggregate interfaces (interfacial transition zone) are modelled as spring layers between the mortar matrix and the inclusions (aggregates) and the existences of the microcracks in the interfacial transition zone are considered as reductions of the spring parameters under the frame of the Mori-Tanaka method. The aligned coalesced cracks in concrete (mortar + aggregate) are treated as void inclusions in the matrix of concrete using the Mori-Tanaka scheme as well. Stochastic evolution rules are adopted for both defects. The numerical examples are worked out and the proposed model is shown to be capable of estimating the moduli of concrete under its whole loading process. Source
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Chase N.J.,Red Cedar Technology |
Averill R.C.,Red Cedar Technology |
Sidhu R.S.,Red Cedar Technology |
Tan J.,Singapore Technologies Engineering
12th AIAA Aviation Technology, Integration and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference | Year: 2012
The aim of this study was to minimize the mass of the structural components in a composite aircraft in order to maximize its payload capacity and flight range. In particular, the detailed lamination schemes in various regions of the fuselage, tail, and wing structural components were optimized using a multi-disciplinary optimization strategy. At every point in the structure, the lamination scheme was defined as an assembly of sublaminates, each of which spanned different regions of the vehicle. The lamination schemes were automatically generated in terms of the sublaminate definitions. Thus, the design variables included the number of plies in each sublaminate and the orientation and material (unidirectional or fabric) in each ply. With hundreds of design variables and a large number of load cases, it was not possible to design an efficient composite aircraft structure using a manual design process and intuition alone. However, by taking advantage of the interactions among the many components, the multi-disciplinary optimization strategy employed here was able to achieve a significant overall mass reduction by making some regions heavier and others lighter. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Source