曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

RMIT, Alpha STAR
Time: November 4, 2009 2:40 pm
Room: Lumen
Physically motivated and empirically validated finite element models are developed for characterizing the
impact damage resistance and compression-after-impact (CAI) residual strength of sandwich composites com30
prised of woven-fabric graphite-epoxy facesheets and Nomex honeycomb cores. A hierarchical micromechanically
based failure technique is employed to predict local composite failure initiation and damage progression/
growth in both facesheets and core. Numerical estimates of impact damage development, obtained using
GENOA/ LS-DYNA, are compared to experimental results for flat sandwich composite specimens subjected
to drop weight normal impact with spherical steel impactors. Here a combination of ultrasonic C-scan images,
visual inspections, and destructive sectioning measurements from the literature are used to assess impact damage.
Impact damage estimates obtained from dynamic impact simulations are used to establish initial conditions
in material and geometric nonlinear GENOA/ ABAQUS finite models aimed at predicting CAI residual
strength; the effect of adhesive (interfacial) failure on damage resistance and CAI strength is also addressed.
Numerical predictions for impact damage resistance, damage progression, and CAI strength are obtained for
a variety of sandwich composite lay-up configurations and over a range of impact velocities and energies,
impactor diameters, and support boundary conditions. Finite element estimates for facesheet surface strains
correlate well with strain gage measurements, as well with strain measurement obtained using the ARAMIS
optical imaging system. Moreover, numerical estimates of CAI residual strength are consistent with experimental
observations.
Title: Trevira CS – Functional Textiles for Aircraft Interiors
Authors: P. Kruecken
Trevira GmbH
Time: November 4, 2009 3:00 pm
Room: Lumen
Perfectly equipped on board
Trevira CS fabrics have many advantages over fabrics made of natural fibres, not only because of their flame
retardant properties but also due to their colour brilliance, low-crease, dimensional stability and anti-abrasion
qualities, not to mention their breathability. The possibility of washing Trevira CS instead of expensive drycleaning
required by alternative products reduces costs significantly. Trevira CS fabrics also offer the potential
for weight reduction compared to other commonly used materials.
Trevira CS Bioactive fabrics are an excellent choice for improving hygiene in aircrafts. Aircraft seats are used
intensively and by many people all over the world. Therefore, it may be reassuring for passengers to know that
every effort has been taken to limit the growth of bacteria in the upholstery. Trevira CS Bioactive fabrics have a
permanent antimicrobial effect preventing odour formation and growth of bacteria in the upholstery. In addition,
they are also flame retardant.
Trevira CS and Trevira CS Bioactive fabrics satisfy the relevant and important international aviation fire protection
standards. The complete range of permanently flame retardant fibres and filaments gives the designers of
aircraft interior fabrics unlimited scope for new patterns, designs and colours. The flame retardant and antimicrobial
modification are built into the Trevira Polyester molecule and are maintained throughout the entire
lifetime of the fabric.
The Trevira fibres and filament yarns are produced in accordance with the highest standards on sustainable
production.
SESSION B2B SYSTEMS AND COMPONENTS
Chair: Prof. J. Narkiewicz (Warsaw University of Technology),
Dr S. Frohriep (Leggett & Platt Automotive Europe)
Title: Architecture Modelling for IMA platform
Authors: M. Fumey
Thales
31
Time: November 4, 2009 1:20 pm
Room: Candela
Title: Avionic Systems Integration through the use of IMA platforms
Authors: G. Romanski
Verocel GmbH
Time: November 4, 2009 1:40 pm
Room: Candela
The extraordinary advances in computer power, memory sizes and Input/Output bandwidth have stimulated
the evolution of Integrated Modular Avionics (IMA) platforms which can support many aircraft functions. These
functions run as applications in one of many virtual target computers provided by the platform. The applications
must co-operate and co-exist even if they are developed by competing suppliers. It is the platform
supplier’s responsibility to provide a development and verification environment such that applications can be
developed and verified independently and then integrated. The integration mechanisms must guarantee that
the verification evidence developed by the application supplier can be carried forward to the system certification
　
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