Aerospace

By his first developments modeFRONTIER was tailored for aerospace experts. Indeed, the optimization framework was born in a European Founded Project whose partners were British Aerospace Systems and DaimlerChrysler Aerospace. Now modeFRONTIER can be considered one of the best software optimizers in the world for Aerospace industries.

Noise Sensitivity Characterization in the Context of the Environmental Design Space
Matthew J. LeVine (School of Aerospace Engineering, Georgia Institute of Technology)
Apr 2012 The international aviation community has grown increasingly interested in the environmental impacts associated with aircraft noise and emissions. Aircraft noise is one of the most significant environmental impacts of aviation, and it is the most common source of complaints from communities, particularly those in close proximity to airports. read on Noise Sensitivity Characterization in the Context of the Environmental Design Space
Structural optimization coupled to fluid-structure interaction of an UAV aircraft wing
Felipe Langelloti Silva
Dec 2011 The main objective of this paper is to study and to propose a methodology in order to obtain an optimized wing structure of the UAV aircraft. Such optimization takes into account the static aeroelastic effects of Fluid-Structure Interaction (FSI) through CFD techniques coupled with FEM. read on Structural optimization coupled to fluid-structure interaction of an UAV aircraft wing
Velocity Impact Damage on a Composite Plate
Rosario Borrelli (CIRA - Italian Aerospace Research Centre)
Dec 2011 Laminate composite structures suffer from poor resistance to impact, resulting in internal damage that often cannot be detected by visual inspection, which may cause severe reductions in strength and increase under load. In order to simulate the impact event the LS-DYNA FE model was developed and coupled with modeFRONTIER. read on Velocity Impact Damage on a Composite Plate
Multidisciplinary Analysis for a Civil Aircraft Conceptual Sizing
Ohad Gur, Gali Lazar, Aharon Yaniv (IAL – Israel Aerospace Industries, Ben-Gurion Airport, Israel), Abhishek Burman (NAL – National Aerospace Laboratories, Bangalore, India)
Nov 2011 This paper focuses on the issue how to decide the aircraft configuration sizing parameters without knowing its appearance and performance, and how to decide its appearance and performance without knowing its sizing parameters. Such decisions can only be taken in a multidisciplinary framework consisting of several software modules, which were integrated into a single synergic tool by means of modeFRONTIER. read on Multidisciplinary Analysis for a Civil Aircraft Conceptual Sizing
Applications of a discrete viscous adjoint method for aerodynamic shape
Joe¨l Brezillon, Richard P. Dwight (Deutsches Zentrum fu¨r Luft- und Raumfahrt)
Oct 2011 This paper describes how the adjoint approach can help the designer to efﬁciently reduce the ﬂow separation onset at wing–fuselage intersection and to optimise the slat and ﬂap positions of a 3D high-lift conﬁguration. The optimisations were performed within a limited number of ﬂow evaluations, emphasising the beneﬁt of the adjoint approach in aircraft shape design. read on Applications of a discrete viscous adjoint method for aerodynamic shape
Efficient Global Optimization Applied to Design and Knowledge Discovery of Supersonic Wing
Masahiro KANAZAKI, Naoto SETO - Tokyo Metropolitan University
Sep 2011 Efficient global optimization (EGO) was applied to the multi-objective design and knowledge discovery of a supersonic transport (SST) wing. The objective functions considered here are employed to maximize the lift-to-drag ratio at supersonic cruise, to minimize the sonic boom intensity and to minimize wing structural weight. read on Efficient Global Optimization Applied to Design and Knowledge Discovery of Supersonic Wing
A New Method to Preliminary Design Structural Components
Michele Ferraiuolo (CIRA-Italian Aerospace Research Centre), Oronzio Manca (Seconda Università di Napoli)
Jul 2011 The aim of the hot structure design process is to ensure the structural integrity of the component minimizing two fundamental parameters: mass and thickness. The former influences the total weight of the vehicle, the latter influences the vehicle efficiency. read on A New Method to Preliminary Design Structural Components
Automated design and fabrication of micro-air vehicles
K. Amadori, D. Lundstro, P. Krus (Linkoping University, Sweden)
Jun 2011 A methodology for an automated design and fabrication of micro-air vehicles (MAVs) is presented. A design optimization framework has been developed that interfaces several software systems to generate MAVs to optimally fulfil specific mission requirements. By means of a multi-objective genetic algorithm, families of MAVs are tailored with respect to objectives such as weight and endurance. read on Automated design and fabrication of micro-air vehicles
Exergonomic Environmental Optimization of Piston-Prop Aircraft
Onder Altuntas, T. Hikmet Karakoc, (Anadolu University, Eskisehir – Turkey), Arif Hepbasli (King Saud University - Saudi Arabia)
Jul 2011 An optimization study is undertaken to find the best results of all of exergy, exergoeconomic and exergo environmental analyses. In this regard, the exergoeconomic environmental optimization of a four-cylinder, spark ignition, naturally aspirated and air-cooled piston-prop aircraft engine is considered first. This is then optimized in the cruise phases. read on Exergonomic Environmental Optimization of Piston-Prop Aircraft
Reliability Based Multidisciplinary Optimization of Aeroelastic Systems
Melike Nikbay, Necati Fakkusoglu, Muhammet N. Kuru (Istanbul Technical University)
Sep 2010 A reliability based multidisciplinary optimization framework is constructed by coupling high-fidelity commercial solvers for aeroelastic analysis and an in-house code developed for reliability analysis. modeFRONTIER is employed as a driver to control the optimization workflow. read on Reliability Based Multidisciplinary Optimization of Aeroelastic Systems
Stochastic improvement of structural design
Soprano Alessandro and Caputo Francesco, in Stochastic Control, edited by Chris Myers
Sep 2010 Design is not an one-step process, but it evolves along many phases which, starting from an initial idea, include drafting, preliminary evaluations, trial and error procedures, verifications and so on. All those steps can include considerations that come from different areas, when functional requirements have to be met which pertain to fields not directly related to the structural one, as it happens for noise, environmental prescriptions and other analysis. read on Stochastic improvement of structural design
Flap Splitting and Setting of the X31 Wing
Stettner, M. and Haase, W., DASA (Germany)
Oct 1999 DASA used modeFRONTIER to optimise the flap splitting (one discrete variable) and the flap settings (two continuous variables) on the X31 wing model. A common requirement for fighter planes is the ability to reach high roll angle accelerations, as this parameter is one of most important determinants of the plane's maneuverability. read on Flap Splitting and Setting of the X31 Wing
Aero-elastic optimization of a composite wing
Schuster,D.M.; Smith,M.J.; Farhat,C.,Lesoinne,M.; Hancox N.l., Rayner M.M.; Osyczka,A.,Kundu,S.
Jun 1997 Over recent decades many new composites have been developed, some with very valuable properties. By carefully choosing the reinforcement, the matrix, and the manufacturing process that brings them together, engineers can tailor the properties to meet specific requirements. They can, for example, make the composite sheet very strong in one direction by aligning the fibres that way, but weaker in another direction where strength is not so important. read on Aero-elastic optimization of a composite wing

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