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									BOOK OF ABSTRACTS
       Eight Pegasus-AIAA

       Student Conference

  Poitiers (France), April 12, 2012
Session:        A                                                               Paper:       1
Time:           11:00 AM

Student Name:   Christine Elisabeth Klei
Institution:    RWTH, Aachen
Country:        Germany
Paper Title:    Investigation of the Recirculation Region of a Generic Rocket Configuration using
                Stereoscopic PIV
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Klei_Aachen.pdf


                                          ABSTRACT

Flow fields with high spatial and temporal dynamics form at the tail section of modern space
transportation systems. Base drag, induced by separating flow regions, decisively influences total
drag values. Wind tunnel experiments at subsonic flow conditions are carried out using a generic
rocket model, simulating an early ascend period. In a first period, a reference model geometry
without nozzle is investigated. Stereoscopic Particle Image Velocimetry is used to characterize
three-dimensional structures of the recirculation area behind the model base. Discrepancies due to
deflections in the angle of yaw are of special interest.
Session:         A                                                                 Paper:        2
Time:            11:30 AM

Student Name:   Francesco Avallone and Carlo Salvatore Greco
Institution:    UniNA Federico II, Naples
Country:        Italy
Paper Title:    2D inverse heat transfer measurements by IR thermography in hypersonic flows
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Avallone_uniNA.pdf


                                            ABSTRACT

The purpose of this work is to develop a data reduction technique for the measurement of heat
fluxes in hypersonic flows. If the temperature gradients in the solid are high enough (e.g. in case of
Gӧrtler vortices that can have high spatial frequency), tangential conduction heat flux in the test
model is not negligible. To estimate the heat flux it has been solved a 2-D inverse heat transfer
problem in which, to reduce the computational cost, the heat flux distribution has been represented
with discrete Fourier series. The data reduction technique has been numerically validated and then
applied to experimental tests performed on a double compression ramp where the instability is
generated using a comb-like strip and several campaign are performed at different pitches of the
teeth. Tests are carried out in the HTFD (Hypersonic Test Facility Delft) hypersonic tunnel at Mach
number equal to 7.5 and at unit Reynolds number equal to 6.61∙106 m-1. The heat flux obtained
solving the 2-D inverse heat transfer problem is compared with the one obtained solving the 1-D
problem to evaluate the effect of the tangential conduction.
Session:         A                                                                  Paper:        3
Time:            12:00 AM

Student Name: Diogo Camello Barros
Institution:     ENSMA, Poitiers
Country:        France
Paper Title:     Passive flow control around a wall-mounted finite cylinder
Paper link: http://www.pegasus-europe.org/AIAA_Pegasus/Papers/DiogoCamello_ENSMA.pdf


                                            ABSTRACT

The present work relates the effect of a straight perturbation on a finite cylinder mounted over a
wall. The aspect ratios studied (length/diameter) are 3 and 6 at Reynolds’ numbers Re of 5.104,
7.104 e 1.105. The influence of a trip wire on the vortex shedding frequencies and flows
modifications generated by different aspect ratios has been analyzed. Averaged drag and lift
coefficients have been measured and the existence of a critical position of the perturbation has been
observed, in which the Strouhal number St and the coefficients vary substantially. Non-stationary
efforts coupled with the fluctuant pressure field on the wall have been measured. The results show
an important correlation between efforts and pressures. The POD (Proper Orthogonal
Decomposition) has been used for the reconstruction of the pressure field and the EPOD (Extended
Proper Orthogonal Decomposition) have pointed the correlated part of the efforts with the pressure
signals. It has been observed that the aspect ratio introduces important differences in the efforts and
pressures measures, changing the recirculation zone around the cylinder. The position of the
perturbation changes significantly the vortex shedding frequency and the mean values of the forces.
The energy of the proper modes and the extended ones shows that a reconstruction of the pressure
or effort field can be done by using two modes.
Session:         A                                                                 Paper:        4
Time:            12:30 AM

Student Name:    Konstantinos Kourtzanidis
Institution:     ISAE, Toulouse
Country:         France
Paper Title:     Numerical Simulation of Plasma Actuators for Flow Control
Paper link:      http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Kourtzanidis_ISAE.pdf


                                            ABSTRACT

As flow control gains more and more interest amongst the aerospace research community, new
methods are arising really fast. This paper deals with the application of plasma actuators to control
the flow over a at surface or an airfoil and more precisely the numerical modelling of them and their
effects in the flow. After a brief introduction to the subject, the models used for the plasma physics
and its coupling with the flow are presented side by side with the meshing procedure. After
validating the capability of the solver with simple cases, different aspects are being examined over a
at plate case such as turbulence and compressibility and compared with experimental data.
Moreover for the same case, a parametric study has been performed for the actuator's inputs as well
as a study on its effects on the laminar to turbulent transition. The actuator has been modelled also
on an airfoil so that more interesting results could be obtained and presented. The mesh generation
and solver's parameters are presented separately for each section.
Session:        A                                                                 Paper:       5
Time:           02:00 PM

Student Name:   Dewi Boucher and H. Guillot
Institution:    Ecole de l’Air, Salon de Provence
Country:        France
Paper Title:    Experimental drag polar of the F-16 Falcon using wind tunnel tests
Paper link:     http http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Boucher_EdA.pdf


                                           ABSTRACT

The aerodynamics of the General Dynamics F-16 Falcon has been studied using experimental and
theoretical methods. Subsonic wind tunnel tests on a 1/48 model of the F-16 were used to determine
the lift and drag on the aircraft at several Mach numbers. The main objective was to determine the
drag polar of the model in several low speed airstream velocities at a Mach number under 0.2 and
then extrapolate the results to a higher Mach number. This experiment has been conducted with
Aerolab wind tunnel of the San Jose State University Aerodynamics Department. The result of the
experiments met the theoretical results of lift and drag on an F-16 fuselage. The performance of the
F-16 is finally discussed using the results on the model.
Session:         A                                                                 Paper:        6
Time:            02:30 PM

Student Name:   Filippo Palo
Institution:    PoliMI, Milano
Country:        Italy
Paper Title:    Wake Models for Real-Time Rotorcraft Simulation
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Palo_PoliMI.pdf


                                            ABSTRACT

The capability of modelling and representing the wake of a rotorcraft is essential to properly
simulate most of the flight conditions, if not all. The accurate representation of the rotor wakes is
still a challenge; notwithstanding the constant increase of computer power, it is still impossible to
perform a complete Free Wake simulation of helicopter rotor wakes in real time. This paper
presents two different ways of tackling the problem, in which the wake model is separated from the
inflow one. The first approach refers to models able to perform accurate analysis in steady flight, in
which the wakes instantly fit to actual flight condition without memory of their previous
configuration. In the second part of the work a dynamic model is formulated and implemented,
termed FastFreeVortex (FFV) rotor wake model. It allows to perform manoeuvring flight analysis,
while respecting the constraint of low computational request, since it may run in real-time on
common desktop machines. The basic element of the FFV model is represented by a set of vortex
rings which constitute the wake. Both models are described and then validated in several
conditions: hover, forward flight, also in ground effect (IGE), and in descent flight, with particular
attention to the ability to intercept the Vortex Ring State (VRS) condition.
Session:        A                                                                 Paper:        7
Time:           03:00 PM

Student Name:   Diliana Dimitrov
Institution:    TU Dresden, Dresden
Country:        Germany
Paper Title:    Unsteady aerodynamics of wings with an oscillating flap in transonic flow
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Dimitrov_Dresden.pdf


                                           ABSTRACT

Within the scope of this paper the behaviour of unsteady flow due to oscillating flaps on the airfoil
NLR 7301 and the AFMP wing is analysed. For the two-dimensional model, the two flow solvers of
DLR (TAU) and ONERA (elsA) are applied. Therefore, a comparison not only with experimental
data but also among both CFD-results is carried out. Although it exists a good agreement for this
two-dimensional experiment and the numerical solutions, differences in the turbulence models of
the codes are exhibited. The three-dimensional delta wing is calculated using TAU. Surprisingly,
the experimental data is only partly reproducible with the CFD code. Despite the existing
discrepancies, the nature of unsteady flow due to an oscillating flap can be found in the experiment
as well as in the numerical results.
Session:        A                                                               Paper:       8
Time:           04:00 PM

Student Name:   Kayo Galem
Institution:    TU Berlin, Berlin
Country:        Germany
Paper Title:    Analysis of Turbulence Accidents based on STAMP and Technical Concepts for
                Mitigation
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Galem_Berlin.pdf


                                          ABSTRACT

Accidents that have resulted from turbulence encounters in scheduled airline flights within the US
airspace between 2000 and 2010 were analyzed. A methodology based on STAMP was developed
for this purpose in order to identify systemic factors in the causal mechanisms of accident
occurrence. Limitations in the processes controlling the safety risk of bodily harm as the
consequence of turbulence in flight operations were revealed by the analysis. Two technical
concepts are proposed to achieve the effective mitigation of this safety risk.
Session:        A                                                               Paper:       9
Time:           04:30 PM

Student Name:   Katerina Petrekova
Institution:    CVUT, Prag
Country:        Czech Republic
Paper Title:    Design of the intelligent tutorial dialogue. New progressive methodology of ATC-
                controller training
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Petrekova_CVUT.pdf


                                          ABSTRACT

The contribution paper deals with the possibility to design and project the new progressive
intelligent communication system between the ATC-controllers and automatic computer pseudo-
pilots for training purposes. This tutorial intelligent dialogue would be applied and consequently
used in the current air traffic procedure systems and methodology of ATC-controllers’ training,
aiming to improve and increase the level of their proficiency abilities, accuracy, and in general,
overall total ATC-controller cadets’ work-scope readiness during training for the ATC-controller
profession.
Session:        A                                                              Paper:       10
Time:           05:00 PM

Student Name:   Oleg Ieremeiev and Alexly Rubel
Institution:    KhAI, Kharkiv
Country:        Ukraine
Paper Title:    Method of estimating UAV flight horizontal velocity using video sequences
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Ieremeiev_Kharkiv.pdf


                                         ABSTRACT

The task of estimating UAV flight velocity using video sequences obtained from on-board video
camera is considered. A method for estimating displacement of X and Y coordinates for adjacent
video frames based on finding similar blocks in two frames with taking into account their
informativity is proposed. To provide an acceptable speed of the method, fast boundary clustering
approach is applied. A test video sequence for verification of methods of motion estimation is
formed. By comparative analysis with well-known methods, it is shown that the proposed method
provides both the best accuracy of the estimates and the smallest number of abnormal estimates.
Session:         B                                                                 Paper:        11
Time:            11:00 AM

Student Name:    Elsa Piollet
Institution:     ISAE, Toulouse
Country:         France
Paper Title:     Mistuning Criticity Assessment for Industrial Single-Piece Single- and Multi-
                 Stage Bladed Assemblies
Paper link:      http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Piollet_ISAE.pdf


                                            ABSTRACT

The aim of the present work is to create a computation chain for multi-stage mistuning study in an
industrial environment. Turbojet engine components are subject to vibration constraints that can
lead to early failure. The need for improved performance with weight-reduced engines has led to
new single-piece multi-stage architectures. Inter-stage couplings in single-piece multi-stage
assemblies can modify the structure's sensitivity to variations in blade properties. These variations,
known as mistuning, can lead to energy localization and early failure due to fatigue. The
computation chain proposed assesses the criticity of random mistuning in industrial multi-stage
bladed assemblies. It is integrated in the industrial software environment. The program is first
validated on an academic case and then applied to an industrial case, leading the way for future
criticity assessments.
Session:        B                                                                 Paper:       12
Time:           11:30 AM

Student Name:   Alfonso Pagani e Matteo Filippi
Institution:    PoliTO, Torino
Country:        Italy
Paper Title:    Advanced Models for Static and Dynamic Analysis of Wing and Fuselage
                Structures
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Pagani_PoliTO.pdf


                                           ABSTRACT

Recently, an hierarchical formulation based on the Carrera Unified Formulation (CUF) was
introduced by adopting polynomial expansions of the displacement field above the cross-section of
the structure. The finite element method was exploited to develop numerical applications by
employing the principle of virtual displacements. In the CUF framework the finite element matrices
and vectors are expressed in terms of fundamental nuclei whose forms do not formally depend on
the order and the class of the model. Two classes of 1D higher-order models have been developed
according to the CUF. The Lagrange Expansion (LE) models were built by means of four- (L4) and
nine-point (L9) Lagrange-type polynomials. The Taylor Expansion (TE) models exploit N-order
Taylor-like polynomials. The classical 1D models are obtained as special cases of TE. This paper
proposes advanced 1D theories for static and dynamic analysis of aeronautical structures. A number
of typical stiffened-shell structures were analyzed. Classical 1D (Euler-Bernoulli and Timoshenko)
and refined models were implemented by exploiting the 1D CUF. Finite element models made with
a commercial software were used for comparison purposes. Results have highlighted the enhanced
capabilities of the present formulation which is able to detect solid and shell-like accuracies with
significantly lower computational costs.
Session:        B                                                                 Paper:       13
Time:           12:00 AM

Student Name:   Krystina Davtian and Vadim Garin
Institution:    KhAI, Kharkiv
Country:        Ukraine
Paper Title:    Problems of recycling constructional polymeric composite materials
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Davtian_Kharkiv.pdf


                                           ABSTRACT

One of the main tendencies in development of aircraft, engineering, transport and other branches is
wider usage of polymeric composite materials (PCM). In comparison with usual constructional
materials polymeric composite materials have considerably higher performance at essentially less
mass. Originally application of PCM in these fields was restrained considering their high cost, PCM
design and manufacture issues as well as problems with attachment of structural units from PCM to
metal parts of an airframe. While solving these problems and PCM cost reducing when organizing
their mass production, application of these materials began to increase rapidly. Additional boost to
PCM implementation in modern aircraft construction was growth of fuel cost. Airframe mass
reduction provided with wide PCM application along with improvement of engine performance is
the main direction of improving fuel efficiency. Intensive usage of composite materials in such
branches of industry as transport, engineering and building has begun due to developing techniques
of design and manufacturing of constructions from composite materials. It is favored by creation of
large-tonnage manufactures of semi-finished products (threads, fabrics and prepregs), thus cost of
composite materials is steadily reduced. The published forecasts of carbon fiber market growth
show that world demand in 2020 can make up to 340 000 tons a year. At the price less than 10 US
dollars per kilo the volume of world consumption of composite materials based on carbon fiber can
rise up to 10 million tons a year in motor industry only. It makes PCM the main constructional
materials of next technological mode. Despite obvious advantages of PCM use there is a problem
constraining its wide application - recycling. The volume of recycling PCM by various estimations
can reach 10...15 % from annual manufacture. This number includes both construction recycling
and PCM wastes. Today in Europe wasters, carbon fiber debris, and other composite production
wastes make up about 500 tons a year, and in the following 15 years it is necessary to recycle from
6000 to 8000 aircraft manufactured with PCM share in the airframe less than 20 % from total mass.
Despite a great number of researches no efficient industrial PCM recycling techniques are
developed so far. The problem is also complicated since many processes in development are
connected with formation of highly toxic compounds. Therefore development of ecologically safe
PCM recycling techniques remains a relevant one and is of practical importance. The purpose of the
given paper is the analysis of modern PCM recycling methods and definition of advanced
approaches for creation of ecologically safe techniques for their recycling.
Session:        B                                                                 Paper:        14
Time:           12:30 AM

Student Name:   Iryna Gagauz
Institution:     KhAI, Kharkiv
Country:        Ukraine
Paper Title:    Investigation of Radiation Influence on Composite Materials
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Gagauz_Kharkiv.pdf


                                           ABSTRACT

Composite materials are gained popularity in a number of industries due to its specific
characteristics. Space industry is one of them where high stiffness, low coefficient of thermal
expansion, and dimensional stability during the operational lifetime as well as minimum weight
solution are required. But spacecraft is exposed to harsh conditions of outer space during the launch
and operation. Properties of composite materials may change due to low earth orbit (LEO) space
environment effect. The purpose of this work to investigate of radiation influence on composite
materials that commonly used in aerospace industry to predict material behaviour in the space.
Session:        B                                                                 Paper:       15
Time:           02:00 PM

Student Name:   Marc Neveu
Institution:    ISAE, Toulouse
Country:        France
Paper Title:    Mapping Trace Gases on Earth, Mars and Beyond with a Gas Correlation
                Radiometer
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Neveu_ISAE.pdf


                                           ABSTRACT

We present results in the development of a miniaturized gas correlation radiometer (GCR),
designed as an orbiting instrument for Earth and planetary science missions. This
instrument will be capable of simultaneously mapping multiple gases in a planet's
atmosphere. Gas correlation radiometry is a mature sensing technology on Earth; successful
miniaturization makes it promising for trace gas measurements in the atmospheres of Mars, Venus,
or Titan. The component that most impacts the size of a gas correlation radiometer is the gas
correlation cell, the pathlength of which affects the sensitivity of the instrument. We use a hollow
waveguide of pathlength equivalent to a 10-meter multipass cell previously flown on Earth
orbit. This results in a cell mass and volume reduction greater than 99%. We present methane
(CH4) and formaldehyde (CH20) measurements from our prototype GCR. This modular
instrument can be expanded to measure additional species of interest, including water vapor
(H20), deuterated water (HD0), nitrous oxide (N20), hydrogen sulfide (H2S), methanol (CH30H),
sulfur dioxide (S02), and carbon dioxide (C02). We review the scientific interest and
spectroscopic feasibility of mapping these gases on different planetary bodies.
Session:        B                                                                 Paper:       16
Time:           02:30 PM

Student Name:   Stefania Soldini
Institution:    PoliMI, Milano
Country:        Italy
Paper Title:    Attitude Dynamics of ESMO Satellite Mass Expulsion Torques and Propellant
                Slosh Model
Paper link:     http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Soldini_PoliMI.pdf


                                           ABSTRACT

This paper deals with the Newton and Euler Dynamics Equations of ESMO, where a mathematical
formulation has been developed. The purpose is to design the internal (non-environmental)
disturbances of the spacecraft, by focusing our attention on the Mass Expulsion Torques and,
primarily, on the Propellant Sloshing effect. Moreover, in order to have an accurate model of the
spacecraft, the dynamics of the reaction wheels have been taken into account as they are part of the
actuators system. A review of the Propellant Sloshing concepts has been investigated, but in this
paper merely the 3D Spherical Pendulum Slosh Model is presented, the one which seemed to be the
most consistent. Furthermore, the Mass Expulsion Torques effects have also been studied in order
to estimate how they affect the attitude of ESMO. In addiction, a consumption model has been
developed so as to estimate the total propellant waste. In that way the inertial properties of ESMO
are not constants anymore and their terms become time depending within the equation of motion.
The primarily interest focused on the internal dynamics since it has been intended to analyze their
effect on the ESMO motion in both its orbit and the attitude dynamics. In the model studied, these
two dynamics equations are uncoupled, in fact the environmental torques, which are usually taken
as coupling terms, have not been considered.
Session:        B                                                                  Paper:       17
Time:           03:00 PM

Student Name: Chiara Finocchietti
Institution:  UniPI, Pisa
Country:      Italy
Paper Title:  Combining Low-Thrust and Manifold Dynamics for Vertical Lyapunov Orbits
              Missions
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Finocchietti_UniPI.pdf


                                           ABSTRACT

With the aim at designing innovative space missions both in terms of operative orbits and transfer
trajectories, this study deals with the Circular Restricted Three Body Problem and its applications.
The vertical Lyapunov orbits, peculiar solutions of the model are computed together with the
ballistic trajectories (manifolds) associated with them. Moreover, with the aim at designing low-fuel
consumption transfer trajectories toward vertical Lyapunov orbits, the combination of the three
body model dynamic and low-thrust transfer strategies is investigated. Finally, the optimization
problem of the low-thrust transfer trajectory is considered and a direct multiple shooting method is
presented for its solution.
Session:        B                                                             Paper:       18
Time:           04:00 PM

Student Name: Tim Dackermann
Institution:  Uni Stuttgart, Stuttgart
Country:      Germany
Paper Title:  Numerical and Analytical Analysis of Voting and Monitoring Mechanisms for
              Different Configurations of Asynchronism
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Dackermann_Stuttgart.pdf


                                         ABSTRACT

The processing of asynchronous redundant information is a basic approach in distributed Avionics
and Flight Control Systems. However, due to asynchronous sampling redundant signals may
deviate among each other and therefore result in unacceptably high monitoring limits for common
voting and monitoring mechanisms. Advanced algorithms aim towards handling asynchronous data
in a more sophisticated way but due to additional complexity the choice for an appropriate
mechanism is not always straightforward. Thus, this paper introduces a model-based evaluation
environment for the objective assessment of voting and monitoring mechanisms. For validation
purposes the environment is verified via numerical and analytical analysis of a selected system
architecture featuring asynchronism.
Session:        B                                                                 Paper:       19
Time:           04:30 PM

Student Name: Jakub Šimánek
Institution:  CVUT, Prague
Country:      Czech Republic
Paper Title:  Analyses of Suboptimal Models for INS/GPS Navigation Algorithms
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Simanek_CVUT.pdf


                                           ABSTRACT

This paper analyses the fusion of an inertial navigation system (INS) and a global positioning
system (GPS) based on various state space models implemented in an extended Kalman filter. A
detailed analysis of navigation performance of three suboptimal INS/GPS models is presented.
Navigation algorithms were implemented in the MATLAB environment and verified under
laboratory conditions using a radio controlled car model with a precise reference trajectory as well
as by field experiments using car navigation.
Session:        B                                                                 Paper:       20
Time:           05:00 PM

Student Name: Ondrej Teren
Institution:  CVUT, Prague
Country:      Czech Republic
Paper Title:  Angular rate reference system employing a fiber optic gyro
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Teren_CVUT.pdf


                                           ABSTRACT

This paper discusses the design of an angular rate reference system. Having a precise angular rate
available during a calibration process is a key issue and in majority cases also very expensive.
There have to be used laser gyroscopes due to their high resolution and sensitivity, stable and low-
level noise outputs. In our case the angular rate reference system uses a fiber optic gyro to
determine an angular rate and also consequently an angle along the vertical axis. Furthermore, the
system employs a dual axis accelerometer in cooperation with dual axis tilt sensor to measure a tilt
of the system, which is crucial to compensate the Earth rotation sensed by the gyro.
Session:         C                                                                  Paper:        21
Time:            11:00 AM

Student Name: Klaus Seywald
Institution:  KTH, Stockholm
Country:      Sweden
Paper Title:  Wingbox Mass Prediction considering Quasi-Static Nonlinear Aeroelasticity
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Seywald_KTH.pdf


                                            ABSTRACT

Nonplanar wing configurations promise a significant improvement of aerodynamic efficiency and
are therefore currently investigated for future aircraft configurations. A reliable mass prediction for
a new wing configuration is of great importance in preliminary aircraft design in order to enable a
holistic assessment of potential benefits and drawbacks. In this thesis, a generic numerical
modelling approach for unconventional wing configurations has been developed and a simulation
tool for their evaluation and mass prediction is implemented. The wingbox is modelled with a
nonlinear finite element beam which is coupled to different low-fidelity aerodynamic methods
obtaining a quasi-static aeroelastic model that considers the redistribution of aerodynamic forces
due to deformation. For the preliminary design of the wingbox various critical loading conditions
according to the Federal Aviation Regulations are taken into account. The simulation tool is
validated for a range of existing aircraft types. Additionally, two unconventional configurations, the
C-wing and the box-wing, are analyzed. The outlook provides suggestions for extensions and
further development of the simulation tool as well as possible model refinements.
Session:         C                                                                  Paper:        22
Time:            11:30 AM

Student Name: Falk Sachs
Institution:  TU Braunschweig, Braunschweig
Country:      Germany
Paper Title:  Development of a reconfiguration concept based on nonlinear inverse dynamics
              using artificial neural networks
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Sachs_Braunschweig.pdf


                                            ABSTRACT

Different approaches of reconfiguration concepts for occurring actuator failures are presented.
These are incorporated into a nonlinear control strategy based on feedback linearization in a
cascaded design of three control loops. The inner loop is augmented with artificial neural networks
(ANN), which counteract existing inversion errors and parameter uncertainties. As a demonstrator,
an unmanned aircraft system (UAS) is chosen, which shows that the reconfiguration works reliably
during fully automatic operation and therefore increases the robustness of existing controller.
Further, the results underline, that the implementation of adaptive ANN in the controller
architecture as well as in the reconfiguration scheme are effective steps to improve the reliability of
fully automatic systems.
Session:         C                                                                  Paper:        23
Time:            12:00 AM

Student Name: Pedro Pablo Guerrero Vela
Institution:  ETSI, Seville
Country:      Spain
Paper Title:  Aero-Structural Airfoil Design Optimisation for Cruising Configuration using
              Tabu Search
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Guerrero_Vela_ETSI.pdf


                                            ABSTRACT

Multi-Disciplinary Design Optimisation is the best approach for finding optimum solutions to real-
world problems, where conflictive requirements from different nature converge. Thus, the
optimisation of such systems represents a really challenging task from a technical point of view. In
this paper, the development of a fully integrated automatic tool for continuous aero-structural wing
design optimisation purposes will be introduced. Five different modules have been configured and
interconnected to make the tool a reality, representing each of them a state-of-the-art application: a)
Multi-Objective Tabu Search (MOTS) a stochastic optimiser enhanced with local search strategies,
b) a parameterisation tool based on Free Form Deformation (FFD) techniques, c) flow analyser
configured for automatic execution, d) in-house fluid-structure interface and e) structural analyser.
An initial optimisation study of a simplified wing based on the Airbus Test Case-A airfoil has been
performed. Two objective functions were assessed, these are: drag to lift coefficient and the
maximum Von Mises stresses that appear at any point on the structure. The preliminary results
reveal the potential of the tool for the successful bi-objective optimisation, demonstrating the
integrity and functionality of the design tool. Outstanding improvements for both objective
functions are found and three different solutions from the Pareto front are analysed and compared
against the datum configuration.
Session:        C                                                                 Paper:        24
Time:           12:30 AM

Student Name: Agnieszka Kwiek
Institution:  WUT, Warsaw
Country:      Poland
Paper Title:  Initial optimization of the strake for the rocket plane
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Kwiek_Warsaw.pdf


                                           ABSTRACT

This paper includes description and results of optimization process of strake shape. The calculations
were conducted for rocket plane whose application will be space tourism. The main problem of the
vehicle during the re-entry flight is a sink rate, in this case lift vortex will be prevent this
phenomenon. The main purpose of this research is improving influence of vortex lift. The
calculations were conducted by software which base on Euler system of equations and multi-grid
scheme. The study focused on high angle of attack cases and subsonic flow. The optimization
process focused on aspect of mechanic of flight, other design problems are omitted.
Session:        C                                                                 Paper:        25
Time:           02:00 PM

Student Name: Daniel Martinez Ruiz
Institution:   ETSIA, Madrid
Country:       Spain
Paper Title:   Mini-Helicon plasma thrusters source study
Paper link:  http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Martinez_Ruiz_ETSIA.pdf


                                           ABSTRACT

In this paper a summary of the energetic study of a mini-Helicon plasma thrusters is presented.
Helicon thrusters are high plasma density - high efficiency devices which are a robust alternative to
current Hall thrusters for long duration space missions. Helicon sources have been used in the past
for material processing. Furthermore, this thrusters does not require a neutralizer for the exhaust
flow, which increases its lifetime considerably. A study over the electromagnetic and fluid power
requirement is carried out to get insight on the power transmission and validate the energetic
viability of the source.
Session:         C                                                                 Paper:        26
Time:            02:30 PM

Student Name: Elena Roibàs Millàn
Institution:   ETSIA, Madrid
Country:       Spain
Paper Title:   Spatial properties of plasmas of low power ring cusp ion thrusters
Paper link:  http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Roibas_Millan_ETSIA.pdf


                                            ABSTRACT

The operation of a gridded, low power ring cusp ion plasma thrusters and the spatial properties of
the emitted plasma plumes are investigated. In this small (5 cm diameter) model, the primary
plasma is produced by a low pressure electric discharge and thermo-ionic electron emitters are
employed for ion beam neutralization. This replaces the currently employed hollow cathodes. This
would allow to decrease the payload weight and the amount of neutral gas used as propellant. The
experimental results point the neutralization process and the ionizing electron production rate by the
cathode as critical issues. Both maximize the outgoing ion current of this throtteable ion thrusters.
Finally, the estimated levels of thrust are found comparable with those of similar devices.
Session:         C                                                                   Paper:        27
Time:            03:00 PM

Student Name: Luciano Fanton
Institution:  PoliMI, Milano
Country:      Italy
Paper Title:  Radiation Effects on Solid Fuel Regression in a Hybrid Micro-Burner
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Fanton_PoliMI.pdf


                                            ABSTRACT

The main hindrance that prevents hybrid rocket propulsion success is the low regression rate of the
solid fuel, that ultimately leads to low engine thrust. In order to avoid this, innovative solid fuel
formulations have been developed, loading HTPB-based solid fuels with energetic additives: in this
work, ballistic characterization of a variety of solid fuels is performed. The effects of radiative heat
transfer on the regression rate is evaluated based on the analytical models available in the literature.
Under the investigated conditions, analysis of experimental data showed a great influence of the
radiative heat due to burnt gases and soot on the regression rate of unloaded and loaded
formulations.
Session:        C                                                                 Paper:       28
Time:           04:00 PM

Student Name: Ruslan Farshatov
Institution:  USATU, Ufa
Country:      Russian Federation
Paper Title:  Modelling of operation processes in gas turbine and rocket engines
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Farshatov_Ufa.pdf


                                           ABSTRACT

For design and operation of various types of engines various modeling systems are used. Modern
modeling systems usually focus on a certain class of objects and tasks to be solved. Thus, the
modeling system DVIGw is designed for thermal gas-dynamic modeling of operation processes in
GTE with various schemes in the zero-dimensional quasi-stationary approximation. Engines of
other types, for example, SFRE even at the early design stage require the use of non-stationary
models. In addition, operation processes in such engines differ from the processes in GTE.
Nevertheless, as is shown below, there is a possibility to unify models of a number of elements that
allows using them for modeling both GTE and SFRE. Addition of new elements to the library
allows expanding modeling system capabilities for analysis in the same environment of both GTE
and SFRE, and in the prospect also rocket engines, internal combustion engine and various
combined engines. This extends the capability of the designer and shows the need for and the
possibility of continuous development of systems simulation in the design process of new aircraft
engines (AE).
Session:        C                                                                 Paper:       29
Time:           04:30 PM

Student Name: Dominik Puckert
Institution:  Uni Stuttgart, Stuttgart
Country:      Germany
Paper Title:  Development of a Cavity Calorimeter for the Inductively Heated Plasma
              Generator IPG6-S
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Puckert_Stuttgart.pdf


                                           ABSTRACT

A cavity calorimeter has been designed, built and set in operation to characterize the inductively
heated plasma generator IPG6-S at the Institute of Space Systems (IRS) at the University of
Stuttgart. IPG6-S is the latest small-scale inductive plasma generator of IRS that enables student
experiments on high-enthalpy plasma flows. These experiments can be simulations of plasma
during planetary re-entry of a spaceship for investigations on thermal protection systems or
fundamental research on catalysis or radiation of plasma states. The cavity calorimeter was built to
determine the mean specific enthalpy and efficiency of the plasma beam and therefore achieve a
first calorimetric and performance characterization. For air as working gas, the mean specific
enthalpy of the plasma beam could experimentally be determined to range from 1 to 13 MJ/kg,
depending on the air mass flow rate and the anode current. Since the mean specific enthalpy of the
plasma flow characterizes the plasma beam’s degree of ionization and dissociation in a
thermodynamic model, important conclusions can be drawn in future experiments regarding the
thermal stress on a spaceship during re-entry. Further, the performance of IPG6-S has been
experimentally quantified by determining a thermal efficiency that achieved values of up to 30%.
At the most efficient working point, the total system efficiency achieved 21%. With these results,
not only a successful first characterization of IPG6-S has been accomplished, but also a basis for
concepts to possibly raise the mean specific enthalpy and efficiencies is being provided.
Session:        C                                                                  Paper:       30
Time:           05:00 PM

Student Name: Arsen Abdulin
Institution:  USATU, Ufa
Country:      Russian Federation
Paper Title:  Numerical simulation of processes in gas turbine combustors
Paper link:   http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Abdulin_Ufa.pdf


                                           ABSTRACT

The verification problems of fluid flow and burning in the elements of the gas turbine combustors is
solved. The simulation of fluid flow in a cylindrical tube using both different turbulence models and
different grid in the boundary layer was carried out; the simulation results are compared with
empirical dependences. In the problem of mixing jets from main holes of the flame tube is chosen
the turbulence model and its adjustment is made. The numerical analysis of air flow in a plane
diffuser was carried out; the results of numerical analysis are compared with the field experiment.
In the problem of the combustion the turbulent eddy dissipation model is chosen, the coefficients
for one-step brutto-reaction are selected, the simulation results are compared with experimental
data. In combustion problems the radiative heat transfer is necessary to taking into account. For the
problems of combustion and flow selection and justification a model of radiative heat transfer is
made. On the basis of the solution of verification tasks the effect of defects in the flame tube and
layer-by-layer cooling sections on the temperature field at the exit of the combustor was modeled.
Session:        C                                                                 Paper:       31
Time:           05:30 PM

Student Name: José Amer Llobera
Institution:   ETSIA, Madrid
Country:        Spain
Paper Title:   Adaptation of the ESPSS/EcosimPro platform for the design and analysis of liquid
               propellant rocket engines
Paper link:  http://www.pegasus-europe.org/AIAA_Pegasus/Papers/Amer_Llobera_ETSIA.pdf


                                           ABSTRACT

The preliminary design of rocket engines has been historically a semi-manual process, where the
specialists work out a start point for the next design steps. Thanks to the capabilities of the
EcosimPro language, such as non causal programming, a natural pre-design model has been
physically discomposed in three modules: propulsion performance, sizing and mass, and mission
requirements. Most of the new stationary capabilities are based on the ESPSS libraries, which are
able to simulate in great detail transient phenomena of fluid systems (e.g. tanks, turbomachinery,
nozzles and combustion chambers). Once the base of the three pre-design modules is detailed, an
effort has been made to determine accurately the mission requirements. For example, in a
geostationary transfer orbit insertion manoeuvre, the maximum change of speed is obtained
considering a finite combustion, instead of the ideal Hohmann transfer orbit. Finally, the model
validation and two application examples are presented: the first one compares the model results
with the real performance of the Aestus pressurized rocket engine. In the second one, the relation
between the initial total vehicle mass and the design parameters (combustion pressure, mixture ratio
and nozzle area ratio) is obtained, looking for an optimized pre-design. And the last one, take
advantage of the ESPSS transient capabilities simulating a transient engine run (startup, manoeuvre
and shutdown), which is used as simplified analysis to verify the optimum pre-design.

								
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