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basic machine functionality and/or vendor specific innovations. Few studies have attempted to create a historic
understanding of how this branch of machinery evolved to its current state. For the current study, various sources
(i.e., scholarly text, trade journals, and patent databases) were examined in order to create the following
historic information: (a) comprehensive equipment definitions, (b) equipment breakdown categorizations, (c)
family trees, and (d) evolutionary timelines covering the past 50 years. The purpose of this study is to provide
foundational information on AMP equipment evolution and future capabilities at a time of economical and
technological change within the commercial aerospace industry.
SESSION B1B IMPROVED SIMULATION
Chair: Albrecht Pfaff (MSC.Software GmbH )
Title: Simulation of aircraft structures using non-linear analysis techniques
Authors: F. Soares (Embraer),
M Lopes de Oliveira e Souza (INPE)
Time: November 4, 2009 10:45 am
Room: Candela
Nonlinear analysis expands engineering capacity to simulate physical problems of structures. The complexity
of new systems requires the usage of more sophisticated simulation techniques to enhance certification process.
Aeronautical structures shall be reliable to comply with certification standards, and they shall be optimized to
fulfill performance requirements. This work explores industry applications and how nonlinear analysis techniques
have been employed on a day-to-day basis of structural analysis. Challenges to improve engineering
simulation are also presented based on industry experience. The focus of this work is the investigation of progressive
failure of composite structures. It is well known that composite materials degradation analysis based
on macromechanical or micromechanical approach plays an important role on progressive failure prediction.
Tailoring geometric instability of reinforced panels such as buckling, postbuckling, mode-jumping and snapthrough
is also important to determine the ultimate load of aircraft structures. This work shows how advanced
finite element tools for certification purpose applied on engineering process have been used to assist engineers
on progressive failure analysis.
Title: Robust Design of Composite Wing Structure, a combined durability and
reliability approach
Authors: F. Rogin, F. Soares, G. Abumeri, Dr F. Abdi (Alpha Star, Embraer),
K. Nikbin (Imperial College)
Time: November 4, 2009 11:05 am
Room: Candela
This paper describes a computational simulation approach devised to perform Robust design of composite
structures that is not sensitive to certain type of failure such as delamination growth. The computational
approach maximizes the durability and damage tolerance (D&DT), and reliability in presence of material ,
fabrication and geometric uncertainties. This computer-based life prediction methodology combines composite
mechanics with finite element analysis, damage and fracture tracking capability, probabilistic analysis, and
robust design optimization algorithm to maximize reliability for given operating condition. NASA Advanced
composite semi wing span structure [Ref 1] developed by Boeing (McDonnell Douglas Aerospace Company)
was successfully proof load tested at NASA Langley. The wing stub box is representative of a section of a
commercial transport aircraft wing. The wing structure for Durability and Damage Tolerance was evaluated
first with finite element based multi-scale progressive failure analysis to determine failure modes, locations and
fracture load. The prediction results were then validated against the Langley test data. Next robust design
optimization is used to maximize the wing structural durability without loss in reliability. The applied computa27
tional process ensures that certain type of failure modes, such as delamination progression, are contained to
reduce risk to the structure. The design enhancement is achieved by tailoring the shape of the wing skin/stiffeners
ratio such as height, width, and the skin thicknesses to absorb the energy that induces delamination. The
application of coupled optimization-probabilistic approach to wing platform shows that the structural reliability
and durability can be simultaneously improved with little or no weight penalty.
Title: Preliminary design of aeroelastic experimental slender wing model
Authors: Prof. G.Frulla , Ing. E.Cestino
Politecnico di Torino
Time: November 4, 2009 11:25 am
Room: Candela
Innovative Aircraft designs, such as very long endurance UAVs have necessitated advances in the methods
of computational aeroelasticity. Analyses procedures for conventional aeroelastic phenomena, such as wing
flutter, also need to be revisited for very flexible aircrafts. In general, the sensitivity of the flutter characteristics
　
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