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capable of generating bank and yaw angles as needed to account for crosswind conditions. Also the vertical
speed is controlled during approach, flare and upon touch-down. Landings are simulated with different values
of the landing mass and the centre of gravity of the aircraft. The influence of flight parameters and the landing
weight on the dynamic behaviour of the landing gear is investigated. Special attention is given to landing gear
oscillations like gear-walk and shimmy vibra-tions. Modelling issues are also considered by comparing landing
gear vibrations for dif-ferent models with increasing number of elastic elements included in the airframe.
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The modular product structure transforms the external variety, which is offered to the customer, to a much lower
internal variety by using few standardised modules. In this context, Lead User Innovations can directly be used
for expanding or adapting the product portfolio of the company. Issue of the paper is a detailed description of
the modular “FlexGalley” product design, as well as the platform definition and technical realisation aspects.
SESSION C3B COMPOSITE STRUCTURES
Chair: Dr. Douglas A. McCarville (Boeing)
Title: Experimenteal and numerical analysis of interlaminar material properties of
carbon fibre composites
Authors: Dr D. Hartung
DLR
Time: November 5, 2009 2:00 pm
Room: Candela
Introduction
Composite are not only used in advanced structures in the aerospace industry, they become more and more
practically be used in classical engineering applications for example the automotive or mechanical industry.
As commonly known composite are particular interesting for lightweight structures because of their advantageous
weight to stiffness and weight to strength ratios. Carbon fibre composites provide highest strength and
stiffness in fibre direction. Despite of these advantageous material properties in fibre directions, the application
of composites is mostly restricted due to relative low material properties perpendicular to that direction. Also
for quasistatic load conditions, the material and failure behaviour of composites is a complex phenomenon, it
dependents on local microscopic damages by low-level load conditions. The load drop of load-displacement
curves correspondent to ultimate material strengths, which are generally higher, compared to damage initiation
limits.
The interlaminar failure between adjacent plies is a common problem of fibre composites especially for thickwalled
structural regions with load introductions. Despite the advantageous strength in fibre direction, the design
and geometry of most structural components are characterised by these interlaminar failure phenomenon.
The interlaminar failure limits are low, compared to the failure limit in fibre direction. The load carrying capability
of thick-walled structures are mainly characterised of the interlaminar material strengths. In order to analyse
the load carrying capability of lightweight structures with critical interlaminare stresses, one have to know the
interlaminar material properties. Furthermore, adequate material and damage models are required. A precise
failure analyse requires the prediction of the damage initiation and particularly the description of a representative
damage evolution function. …
Title: Fire resistant epoxy composites
Authors: Dr M. Heneczkowski , Prof.H.Galina, Dr M. Oleksy
Rzeszow University of Technology
Time: November 5, 2009 2:20 pm
Room: Candela
Epoxy resins and other thermoset matrices are used for fabrication of aircraft composite structures reinforced
with glass, carbon, boron and/or aramides fibres. Growing number of published reports and patents demonstrate
increasing interest in environment friendly flame retardants for these materials. Phosphorus-containing
compounds incorporated into epoxy resins network as comonomers and/or crosslinking agents are more and
more often used to improve the flame resistance of polymer based composites.
Some attention attracted recently also quaternary ammonium salts (QAS) modified montmorillonite clays (organoclays)
that serve as nanoparticles improving mechanical, thermal and fire resistant properties of thermoset
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matrices. It was found that the best effect of organoclays addition is observed when exfoliated structure of composite
is obtained.
In our investigation we used natural bentonites S and SN (purified and enriched in montmorillonite, produced
by ZGM “Zebiec” – Poland) modified with benzyl-alkyl- dimethylammonium chloride. Composites of epoxy
resin (Epidian 6, liquid bisphenol A resin produced by “Organika-Sarzyna”, Poland) and 0.5, 1.0, 3.0 and
5.0 wt% of organoclay cured with triethylenetetramine were obtained. Fire resistance of composites specimens
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