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  • 1.
    Girodroux-Lavigne, P.
    et al.
    ONERA, DDSS/MS, BP72, 92322 Châtillon Cedex, France.
    Grisval, J.P.
    ONERA, DDSS/MS, BP72, 92322 Châtillon Cedex, France.
    Guillemot, S.
    DASSAULT Aviation, DGT/DTA/IAP, 92214, Saint-Cloud Cedex, France.
    Henshaw, M.
    BAE Systems, Aerodynamic Technology Dept., Brough, E. Yorks, United Kingdom.
    Karlsson, A.
    Selmin, V.
    ALENIA Aeronautica, 10146 Torino, Italy.
    Smith, J.
    FOI Swedish Defence Research Agency, FFA Aeronautics Division, 17290 Stockholm, Sweden.
    Teupootahiti, E.
    DASSAULT Aviation, DGT/DTA/IAP, 92214, Saint-Cloud Cedex, France.
    Winzell, B.
    Comparison of static and dynamic fluid-structure interaction solutions in the case of a highly flexible modern transport aircraft wing2003Ingår i: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 7, nr 2, s. 121-133Artikel i tidskrift (Refereegranskat)
    Abstract [en]

    This paper describes the computational work performed by five of the fifteen partners in the Brite-Euram project UNSI, for the prediction of static aeroelastic configurations and dynamic flutter response at transonic conditions, using advanced time-domain fluid-structure coupling methods. The aerodynamic models, mechanical models, and coupling strategies implemented in the different solvers are presented. A code to code validation of the fluid-structure coupled solvers has been achieved in the case of the highly flexible MDO wing. The coupled codes have each been used first for the computation of steady state flow and static deformations at different flight conditions. The investigation of flutter has been carried out for off-design, heavy-cruise flight conditions, using time-consistent numerical simulations. Dynamic responses have been recorded and compared for stable and flutter conditions. © 2002 Éditions scientifiques et médicales Elsevier SAS. All rights reserved.

  • 2. Gledhill, Igle M. A.
    et al.
    Forsberg, Karl
    Eliasson, Peter
    Baloyi, Jeffrey
    Nordström, Jan
    Uppsala universitet, Avdelningen för teknisk databehandling.
    Investigation of acceleration effects on missile aerodynamics using computational fluid dynamics2009Ingår i: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 13, s. 197-203Artikel i tidskrift (Refereegranskat)
  • 3.
    Kapidzic, Zlatan
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Hållfasthetslära. Linköpings universitet, Tekniska högskolan.
    Nilsson, Larsgunnar
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Hållfasthetslära. Linköpings universitet, Tekniska högskolan.
    Ansell, Hans
    Saab AB, Linköping, Sweden.
    Conceptual studies of a composite-aluminum hybrid wing box demonstrator2014Ingår i: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 32, nr 1, s. 42-50Artikel i tidskrift (Refereegranskat)
    Abstract [en]

    This paper presents a study of two different hybrid composite-aluminum concepts applied to a winglike structure which is exposed to mechanical  and thermal load. The aim of the study is to determine the most suitable  hybrid concept to later on be used in structural fatigue and static testing. In both concepts, the mass is optimized with respect to two different sets of requirements, one of which is currently in use in the fighter aircraft industry and one which is a modified version of the current requirement set. The issues considered in the study are mass, thermal behavior, buckling, bolted joints, failure criteria and fatigue damage, and they are examined in the frame of both requirement sets. The results clearly indicate the order of criticality between the different criteria in the different parts of each concept. Also, the comparison of two requirement sets gives an idea of the degree of influence of the modified criteria on the hybrid concepts and their mass. Based on the mass and the structural behavior in a thermal-mechanical loading one of the hybrid concepts is chosen for further studies and testing.

  • 4.
    Marcus, Carina
    et al.
    Linköpings universitet, Institutionen för fysik, kemi och biologi, Teoretisk Fysik. Linköpings universitet, Tekniska fakulteten. Saab AB, SE-58188 Linkoping, Sweden.
    Andersson, Kent
    Swedish Def University, Sweden; National Def University, Finland.
    Åkerlind, Christina
    Linköpings universitet, Institutionen för fysik, kemi och biologi, Tunnfilmsfysik. Linköpings universitet, Tekniska fakulteten. Swedish Def Research Agency, Sweden.
    Balancing the radar and long wavelength infrared signature properties in concept analysis of combat aircraft - A proof of concept2017Ingår i: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 71, s. 733-741Artikel i tidskrift (Refereegranskat)
    Abstract [en]

    Designing combat aircraft with high military effectiveness, affordability and military suitability requires balancing the efforts of many engineering disciplines during all phases of the development. One particular challenge is aircraft survivability, the aircrafts ability to avoid or withstand hostile actions. Signature management is one way of increasing the survivability by improving the ability to avoid detection. Here, the long-wave infrared and radar signatures are studied simultaneously in a mission context. By establishing a system of systems approach at mission system level, the risk of sub optimization at a technical level is greatly reduced. A relevant scenario is presented where the aim is to incapacitate an air-defense system using three different tactics: A low-altitude cruise missile option, a low and medium altitude combat aircraft option. The technical sub-models, i.e. the properties of the signatures, the weapons and the sensors are modeled to a level suitable for early concept development. The results from the scenario simulations are useful for a relative comparison of properties. Depending on the situation, first detection is made by either radar or infrared sensors. Although the modeling is basic, the complexity of the infrared signature and detection chain is demonstrated and possible pivot points for the balancing of radar and IR signature requirements are identified. The evaluation methodology can be used for qualitative evaluation of aircraft concepts at different design phases, provided that the technical models are adapted to a suitable level of detail. (C) 2017 Elsevier Masson SAS. All rights reserved.

  • 5.
    Young, T.
    et al.
    Department of Mechanical Engineering, University of Limerick, Limerick, Ireland.
    Mahony, B.
    Department of Mechanical Engineering, University of Limerick, Limerick, Ireland.
    Humphreys, B.
    Aerospace Systems and Technology, Consett, Durham, United Kingdom.
    Totland, E.
    McClafferty, A.
    Department of Mechanical Engineering, University of Limerick, Limerick, Ireland.
    Corish, J.
    Department of Mechanical Engineering, University of Limerick, Limerick, Ireland.
    Durability of hybrid laminar flow control (HLFC) surfaces2003Ingår i: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 7, nr 3, s. 181-190Artikel i tidskrift (Refereegranskat)
    Abstract [en]

    As a part of the European Commission sponsored HYLTEC (Hybrid Laminar Flow Technology) project, a SAAB 2000 aircraft - fitted with a number of small laser drilled panels on the wing leading edge - completed 20 months of routine service, the objective being to investigate contamination and durability aspects of Hybrid Laminar Flow Control (HLFC) suction surfaces. A post-flight test investigation of these panels, manufactured from Nd-YAG laser drilled titanium, aluminium and carbon fibre polyetheretherketone (PEEK) composite, has been conducted. Using Scanning Electron Microscopy (SEM), evidence of corrosion and damage was investigated. An optical inspection technique was used to measure hole geometries and the results were compared to pressure loss measurements through the panels. Titanium was found to be the most robust material, displaying no adverse affect from this exposure, whilst aluminium was found to be substantially less durable. The PEEK carbon fibre composite showed signs of surface degradation after only two months of flight trials. © 2003 Éditions scientifiques et médicales Elsevier SAS. All rights reserved.

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