PAPERS 12th PEGASUS-AIAA Student conference 2016

363 Pages·2016·54.77 MB·English

PAPERS
12th PEGASUS-AIAA
Student conference
April 20th-22nd, 2016, Valencia
1
7
FINITE ELEMENT ANALYSIS OF THERMOELECTRIC-
GALVANOMAGNETIC INTERACTIONS AND THEIR AEROSPACE
APPLICATIONS
Said Abouali Sánchez, J.L. Pérez-Aparicio, R. Palma
Universitat Politècnica de València (UPV), ETSID, Valencia, Spain

18
Heat Transfer within the CubeSat MIST
A. Berggren
KTH Royal Institute of Technology, Stockholm, SE-100 44, Sweden

27
Vision-Based Navigation for Proximity Operations Around Asteroids
Vincent Bissonnette
Institut Supérieur de l’Aéronautique et de l’Espace, Toulouse, 31400, France

38
Fixed-wing UAV performance flight testing
Federico Bus and Lorenzo Trainelli
Politecnico di Milano, Milano, Italy

49
Analysis of signal interruption during atmospheric re-entry phase of a space
mission
Matteo Caldaroni
University of Rome “La Sapienza”, Rome, 00185, Italy

60
Electron cooling effect on magnetized plasma expansions
Sara Correyero Plaza
Universidad Politécnica de Madrid, Madrid, Spain

71
Parallel implementation of compact schemes with good spectral properties for
flow simulations
Enrico M. De Angelis
Università degli studi di Napoli “Federico II”, Naples, 80125, Italy

82
Attitude Determination and Control of Micro-Satellite RISESAT for Satellite-
to-Ground Optical Communication Experiments
Arianna Dorsa1, Pietro Pagani, Prof. Franco Bernelli Zazzera
Politecnico di Milano, Milan, I-20156, Italy
and
Prof. Toshinori Kuwahara
Tohoku University, Sendai, Japan

93
Development of an academic tool for the design and performance analysis of
airplanes on a project based learning context
P. Fernandez-Golbano and S. Esteban
University of Seville, Seville, Spain, 41092
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104
Simulation of the Aerodynamic Characteristics of a Cycloidal Rotor in
Forward Flight using CFD.
Liam Ferrier
University of Glasgow, Glasgow, G12 8QQ, Scotland

115
Strength analysis of metal-to-composite semi-loop joint
Oleksandr Fomenko,
National Aerospace University “KhAI”, Kharkiv, Ukraine
Supervisor
Ph.D. Maryna Shevtsova
National Aerospace University “KhAI”, Kharkiv, Ukraine

121
Importing Energy by LNG fueled aircraft into Japan
Diego Fuerte Sanz
Universidad Politécnica de Madrid, Escuela Técnica Superior de Ingenieros
Aeronáuticos Spain

132
Aerodynamic Analysis of the Engines’ Integration on a Blended Wing Body
Aircraft
V. Gorrachategui
Technical University of Madrid (UPM), 28040 Madrid, Spain

144
Feasibility Study of a CubeSat mission through orbital simulation in
MatlabTM
Oscar Hag
Royal Institute of Technology (KTH), Stockholm, 100 44, Sweden

154
Development of 3D printed UAV platform
J. Kerner and M. Mondek
Students, Department of Control Engineering, Faculty of Electrical Engineering,
Czech Technical University in Prague, CZ

159

Temperature Measurements in Correlation with HeatTransfer
Sous-Lieutenant LECORRE Kevin and Sous-Lieutenant BAULU Matthieu
French Air Force Academy, Salon-de-Provence, 13300, FRANCE
Ph.D. SEMPER Michael and Ph.D. ABATE Gregg
Department of Aeronautics, United States Air Force Academy, 80841, USA

168

Mission Safety Analysis for Tethered Active Space Debris Removal
H. T. K. Linskens and E. Mooij
Delft University of Technology, Faculty of Aerospace Engineering, Kluyverweg 1,
2629 HS Delft, The Netherlands

PAPERS 12th PEGASUS-AIAA Student conference 3
179
Guidance and Control Algorithms for Space Rendezvous and Docking
Maneuvers
Mammarella M.
Politecnico di Torino, Turin, Italy

190
Guidance Navigation and Control Techniques for 4D Trajectory Optimization
Satisfying Waypoint and No-Fly Zone Constraints
Daniele Giuseppe Mazzotta
Politecnico di Torino, Turin, Italy, 10129

201
Electrohydrodynamic thrust for in-atmosphere propulsion
N. Monrolin
ISAE (Institut Supérieur de l’Aéronautique et de l’Espace), Toulouse, France, 31055
IMFT (Institut de Mécanique des Fluides de Toulouse), Toulouse, France, 31400.
F. Plouraboué and O. Praud
IMFT (Institut de Mécanique des Fluides de Toulouse), Toulouse, France, 31400.

212
Finite Element Optimization of Thermoelectric Coolers
Pablo Moreno Navarro
Universitat Politècnica de València, Valencia, 46022, Spain.

222
Modern SmallSat Launch Options Research.
Elena Petrakova
Moscow Aviation Institute, Moscow, Russia, 125993

233
Vortex forcing resulting from the interaction between two airfoils
Quintens H., Faure T.M., Montagnier O., Hétru. L.
Centre de Recherche de l’Armée de l’air (CReA)

245
Aeroacoustic Optimization of a Low Speed Fan
João Miguel Rebelo Branco
[email protected]
Instituto Superior Técnico, Lisboa, Portugal

255
Analysis and Optimization of an Autopilot for the Civil Airborne Utility
Platform S15 LAPAZ
Julian Rhein
Technical University of Berlin, Berlin, Germany

266
A dynamically coupled model for maneuvering flexible aircraft
F. Saltari
Sapienza University of Rome, Rome, Italy, 00184

PAPERS 12th PEGASUS-AIAA Student conference 4
277
Structural Dynamics for Aeroelastic Analysis
João Daniel dos Santos Almeida
[email protected]
Instituto Superior Técnico, Lisboa, Portugal

287
Boundary Layer Control Device by Blowing Exhaust in an Airfoil Profile
Sanz-Rupérez, J. M.
Student at Universitat Politècnica de València, Valencia, Comunidad Valenciana,
Spain

298
Optical Investigation of a Water Spray Controlled by a Synthetic Jet Actuator
Vincenzo Sepe
Università degli Studi di Napoli “Federico II”, Department of Industrial
Engineering, Naples, Italy

309
Dual-properties disks: toward a spatial optimization of mechanical properties
for better operating conditions in the hot sections of gas turbines
Hesser Taboada Michel
Institut Pprime, UPR CNRS 3346, Physics and Mechanics of Materials Department,
ISAE-ENSMA, Futuroscope - Chasseneuil, 86961, France
Jonathan Cormier and Patrick Villechaise
Institut Pprime, UPR CNRS 3346, Physics and Mechanics of Materials Department,
ISAE-ENSMA, Futuroscope - Chasseneuil, 86961, France
and
Christian Dumont
Aubert & Duval, site des Ancizes, Research and Development Department, BP1,
63770 Les Ancizes Cedex, France

320
Multi-objective optimization for the design of a High-Altitude Long-Endurance
unmanned vehicle
Lorenzo Maria Travaglini
Sapienza-Università di Roma, Rome, Italy, 00184

331
Early and robust detection of Oscillatory Failure Cases (OFC) in the flight
control system: a data driven technique
S.Urbano
ISAE, Toulouse, France, 31055
P. Goupil
AIRBUS, Toulouse, France, 31060
E. Chaumette
ISAE, Toulouse, France, 31055

342
System Identification using the Multivariate Simplotope B-Spline
T. Visser, C. C. de Visser and E. van Kampen
Delft University of Technology, P.O. Box 5058, 2600 GB Delft, The Netherlands

PAPERS 12th PEGASUS-AIAA Student conference 5
353
Operational support to a mission in preparation: development of the LEOP
Timeline Tool and the On-Board Control Procedures library for the Sentinel-3
Mission Control Team
Franco Zurletti
Politecnico di Torino, Turin 10100, Italy

PAPERS 12th PEGASUS-AIAA Student conference 6
FINITE ELEMENT ANALYSIS OF
THERMOELECTRIC-GALVANOMAGNETIC
INTERACTIONS AND THEIR AEROSPACE
APPLICATIONS 1
Said Abouali S´anchez2, J.L. P´erez-Aparicio 3, R. Palma 4
Universidad Polit´ecnica de Valencia (UPV), ETSID, Valencia, Spain
The technology used in aerospace applications is very advanced regarding
performance and e↵ectiveness; however, the aerospace field is under continuous
improvement. In particular, some of the main current goals are related to the
reduction of costs and the building of more eco-friendly aircraft and spacecrafts.
One possible way to achieve these objectives is the use of thermoelectric devices.
Throughout this work the thermoelectric e↵ects and their practical applications
are introduced. Moreover, how the prescription of a magnetic field can improve
the performance of the systems that take advantage of these e↵ects is studied.
A study of the thermoelectric, thermomagnetic and galvanomagnetic e↵ects and
their interaction is performed and their applications in the aerospace and aero-
nautic field are considered. The COP (Coe�cient of Performance), an estimator
of the e�ciency, with and without magnetic field is analyzed.
1 Introduction to thermoelectric e↵ects
Thermoelectric e↵ect is the conversion of temperature T gradients to voltage V drops
and vice versa. There are four thermoelectric e↵ects (Seebeck, Peltier, Thomson and Joule)
that can be used both for power generation or for refrigeration. Military and aerospace are
the most dominant markets for thermoelectric energy harvesting.
Figure 1: Thermoelectric Energy Generator that powers NASA’s Mars Rover, Curiosity.
1This paper is based upon the author’s aerospace bachelor’s thesis
2Author: Department of Continuum Mechanics and Theory of Structures, UPV, Spain
3Supervisor: Department of Continuum Mechanics and Theory of Structures, UPV, Spain
4Supervisor: Department of Mechanical Engineering and Construction, UJI, Castell´on de la Plana, Spain
1
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For example, commercial and military aircraft incorporate sensors and sensor networks
powered by thermoelectric generators to monitor the aircraft skin for damage that can cause
stresses and structural weakness. Taking advantage of the conversion of energy and heat
wastes into electrical energy, aircraft are able to produce energy for on-board applications.
Ontheotherside, hotpointscanberefrigeratedifanelectricfluxisprescribed(Peltiercells).
In the aerospace sector, the Mars Curiosity Rover, Galileo satellites or Cassini spacecraft
amongothersareallusersofThermoelectricEnergyGenerators. Thesevehiclestakeprofitof
the electric power generated by means of an RTG (Radioisotope Thermoelectric Generator,
shown in Figure 1). In one of the sides of the RTG a radioisotope is producing heat and
therefore a high temperature. The other side is not in contact with the vehicle and ideally
hidden from the sun radiation, being therefore colder. That temperature gradient is con-
verted into electrical power thanks to the use of thermoelectric devices.
Thermoelectric energy harvesting presents several advantages. TEGs can be used au-
tonomously to power wireless sensor networks, and are particularly in demand where there
is no constant power source, the access for maintenance or changing a battery is impractical,
other sources of ambient energy are not consistent or there are hostile environments. Ad-
ditionally, TEGs do not use liquids, get better in high temperatures and are not reliant on
sunlight (like solar) or movement (piezoelectric). Indeed, is due to all these features why
TEGs are perfect for use in space applications.
Nevertheless, these e↵ects are not completely consolidated due to their low e�ciency.
Current researches in the thermoelectric field, such as use of graded materials or nanotech-
nology, are focusing on improving their e�ciency. In this work, one innovative solution is
proposed: magnetic fields. The prescription of a magnetic field B may improve the thermo-
electric response and e�ciency since new e↵ects appear: thermogalvanomagnetic e↵ects, the
interaction between the thermal, electric and magnetic field. In this paper, the e↵ects are
studied in the refrigeration mode (Peltier cells), but the application would be similar for the
generation mode (RTG).
2 Thermoelectric and thermogalvanomagnetic formulation
In this section, the mathematical formulation of thermoelectric e↵ects is introduced and
then modified to couple the e↵ect of a magnetic field. This is done with the objective of
performing a finite element analysis of this phenomena.
2.1 Thermoelectric formulation
The thermoelectric balance equations, developed in [1] and [2] and shown in (1), relate
the thermal and electric fluxes with the temperature and voltage gradients.
j = � V � ↵ T
� ·r � · ·r
8 Ohm Seebeck (1)
>>> q =| {z T}+↵| j{zT }
< � ·r · ·
Fourier Peltier
>
>
>: | {z } | {z }
2
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where�(T), (T)aretheelectricandthermalconductivitiesrespectivelyand↵(T)istheSee-
beck coe�cient. The Ohm and Fourier terms are present for every material, but the Seebeck
and Peltier terms are only activated in thermoelectric materials and they are responsible for
the generation of energy and refrigeration.
2.2 Thermoelectric Peltier cell
A thermoelectric Peltier cell, whose main goal is cooling, is composed of several thermo-
couples, each of them formed by two thermoelements (InSb for this work), one of p-type and
other of n-type.
Figure 2: Scheme of the thermocouple functioning.
Figure 2 shows the schematic functioning of a thermocouple. Heat fluxes are created in
vertical direction since the application of a voltage di↵erence activates the thermoelectric
terms of equation (1) and the cold face is refrigerated.
The Coe�cient of Performance (COP) is defined as the ratio between the extracted heat
and the input electric power, as shown in equation (2):
Q
c
COP = (2)
V I
tec tec
2.3 Thermogalvanomagnetic formulation (Thermoelectric + B)
When a magnetic field B is prescribed, the balance equations, developed in [3], become as
(3):
3
PAPERS 12th PEGASUS-AIAA Student conference 9
j = � V � ↵ T
� ·r � · ·r
(3)
8
q =  T +↵ j T
<
� ·r · ·
where�,and↵aretensorsinsteadofcoe�cients(astheywerewhentherewasnotmagnetic
:
field), and they can be written, according to Landau formulation, as (4):
↵ NB NB
z y
�
↵ = NB ↵ NB
z x
2 � 3
NB NB ↵
y x
�
4 5
⇢ RB RB
z y
�
⇢ = RB ⇢ RB (4)
z x
2 � 3
RB RB ⇢
y x
�
4 5
MB MB
z y
�
 = MB MB
z x
2� 3
MB MB 
y x
�
4 5
where N(T), R(T) and M(T) are the Nernst-Ettinghausen, Hall and Righi-Leduc thermo-
galvanomagnetic coe�cients and they activate the o↵-diagonal terms of the tensors, coupling
the three dimensions of space and inducing perpendicular temperature and voltage gradients.
The four thermogalvanomagnetic e↵ects are:
Hall: in the presence of a magnetic field, an electric flux induces a voltage gradient
•
perpendicular to the magnetic field and to the electric flux
Ettinghausen: inthepresenceofamagneticfield, anelectricfluxinducesatemperature
•
gradient perpendicular to the magnetic field and to the electric flux
Nernst: in the presence of a magnetic field, a heat flux induces a voltage gradient
•
perpendicular to the magnetic field and to the heat flux
Righi-Leduc: in the presence of a magnetic field, a heat flux induces a temperature
•
gradient perpendicular to the magnetic field and to the heat flux
If the magnetic field is applied in the proper direction, these perpendicular e↵ects are
in charge of improving the COP of the thermocouple shown in Figure 2 because they may
increase the temperature gradients (increasing the numerator of equation (2)) and decrease
the voltage gradients (reducing the denominator).
2.4 Finite element analysis
Thesetofequations(3)togetherwiththeequilibriumequationsandtheproperboundary
conditions close the finite element analysis problem (see [3] and [4] for detailed information).
The program used is FEAP, a research program developed by Berkeley University. The
elements are self programmed by the user and include all the interactions explained as well
astheelasticonetoobtainthestressfield. Notethatsincetheelementhasbeenprogrammed
by the user, a validation that compares the FEM solution with the analytical one is needed
(developed in [4]). Some simulation results may be found in next sections. For the complete
finite element analysis of the thermogalvanomagnetic interactions see [4].
4
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