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InternacionalTipo de proyectoEntidad financiadoraNacionalidad EntidadTamao de la entidadFecha concesin
ParticipantesOtros Participantesx GENERACION PARAMETRICA DE FORMAS DE EMBARCACIONES RAPIDAS MEDIANTE SUPERFICIES NURBS PARA SU OPTIMIZACION HIDRODINAMICAEl objetivo principal de este proyecto es en el desarrollo de nuevas herramientas y tcnicas
de generacin automtica de las formas de una embarcacin rpida, utilizando para ello
parmetros significativos del casco del buque. Estas nuevas tcnicas permitirn al diseador
de embarcaciones rpidas tener una nueva herramienta de diseo que permita agilizar su
flujo de trabajo. Estos parmetros marcarn las propiedades fsicas, hidrodinmicas y de
estabilidad de la embarcacin.
0<Proyectos y convenios en convocatorias pblicas competitivas'Ministerio de Economa y CompetitividadESPAAGran Empresa (>250)
01/01/2016Director: Leonardo Fernandez Jambrina//Codirector: Francisco Lazaro Perez Arribas//Participante: Alicia Canton Pire//Participante: Luis Perez Rojas//Participante: Antonio Rodriguez Goi//Participante: Maria Eugenia Rosado Maria//Participante: Maria Jesus Vazquez Gallo//ACTIVIDADES DE SEGUIMIENTO DE LA FUSION NUCLEAR POR CONFINAMIENTO INERCIAL (IFE) PARA LA PRODUCCION DE ENERGIA DE LA U.E. CONVENIO 01/280HProcesos fsicos en fusin inercial y esquemas alternativos de ignicin.1Otros tipos de proyectos(Asociacin EURATOM/CIEMAT para la FusinDesconocidoDirector: Fco. Javier Sanz Recio//Participante: Jose Javier Honrubia Checa//Participante: Luis Felipe Ibaez Gonzalez//Participante: Rafael Ramis Abril//cAPiS: Anlisis dinmico, propagacin orbital avanzada y simulacin de sistemas espaciales complejosSin nacionalidad
17/11/2014gDirector: Jesus Pelaez Alvarez//Participante: Oscar Lopez Rebollal//Participante: Manuel Ruiz Delgado//BOOSTERQC: Mejora de la conversin de energa solar mediante procesos de excitacin electrnica en dos etapas: Clculos Cunticos
01/08/2014IParticipante: Pablo Palacios Clemente//Director: Perla Wahnon Benarroch//0Participante: Eduardo Ariel Menndez Proupin //gCooperacin en el diseo y desarrollo de sistemas de mecanismos para aplicaciones espaciales.(prrroga)ERealizacin de trabajos cientficotcnicos en el marco del proyecto.Proyectos y convenios de financiacin privadaEADS
08/02/2016RDirector: Consuelo Fernandez Jimenez//Participante: Maria Laura Hernando Guadao//oCooperacin en el diseo y desarrollo de sistemas de soluciones de control trmico para aplicaciones espaciales
20/01/2016xDHPOPLAS: Desarrollo y caracterizacin de un sistema hbrido de propulsin espacial por plasma de bajo consumo elctricoDirector: Luis Conde Lopez//Participante: Jose Manuel Donoso Vargas//Participante: Ezequiel Del Rio Fernandez//Participante: Juan Luis Domenech Garret//Participante: Joseba Izaga Ugarriza //Participante: Jos Ramn Ferrer Villanueva //Participante: Luis Manuel Snchez Ruz //Participante: Jos Luis Simn //Participante: IGOR MIJAIL TKACHENKO GORSKI //4Environmental aspects of passive deorbiting devicesLas velas y amarras electrodinmicas son candidatos para bajar los satlites cuando stos han terminado su misin. En este proyecto se evala su impacto ambiental debido a su posible colisin con la basura espacial.Agencia Espacial Europea
27/01/2017NDirector: Ricardo Angel GarciaPelayo Novo//Codirector: Claudio Bombardelli //FEXPLORING ANGULARMOMENTUM PHENOMENOLOGY IN AEROTHERMODYNAMICS AND MHD"Exploring angular momentum phenomenology in aerothermodynamics and MHD". The objective of this activity is to revisit and, if needed, to investigate at deeper level the Angular Momentum (AM) phenomenology in fluid dynamics. Task 1: Extension of perfectgas model to include AM state parameter. The standard procedure to obtain partition functions in statistical thermodynamics must be revisited and extended to account for the AM state parameter (UPMESA) Task 2: Flowfield computation with standard NavierStokes constitutive equations. A standard NavierStokes computation of the flow field for the defined test case must be carried out through a stateoftheart CFD flow solver. (DLRUPM) Task 3: Flowfield computation with AMmodified NavierStokes constitutive equations. The flowfield governing equations, the thermodynamic model and the constitutive equations that account for the AM phenomenology must be implemented in the CFD flow solver already used. (DLR,St. Petersburg University).A falta de descripcinESAHOLANDAPAISES BAJOS
11/06/2015IDirector: Jose Manuel Donoso Vargas//Participante: Jorge Gonzalez Muoz//jGCCIES. MATERIALES, DISPOSITIVOS Y TECNOLOGA PARA EL DESARROLLO DE LA INDUSTRIA FOTOVOLTAICA (MADRIDPV)bMATERIALES, DISPOSITIVOS Y TECNOLOGA PARA EL DESARROLLO DE LA INDUSTRIA FOTOVOLTAICA (MADRIDPV) COMUNIDAD DE MADRID
11/11/2014IDirector: Perla Wahnon Benarroch//Participante: Pablo Palacios Clemente//OLEOSWEEP: Improving Low Earth Orbit Security With Enhanced Electric Propulsion
The total mass of space debris in the low Earth orbit region is estimated to be close to 2,500 tons. About half of this mass is composed by rocket upper stages clustered in high inclination orbital regions. Because they are grouped in a relatively small number of families, acquiring the capability to deorbit just a few upper stage types would lead the way towards the elimination of hundreds of tons of debris material in the future. The goal of the LEOSWEEP project (improving Low Earth Orbit Security With Enhanced Electric Propulsion) is to demonstrate the technological feasibility of a first active removal mission of a Ukrainian rocket upper stage, prove its economic viability, and propose a convincing legal and policy implementation to “kickstart” largescale active debris removal activities in Ukraine, Europe and other space faring nations in the future.
The recently proposed Ion Beam Shepherd (IBS) concept is employed as the key removal technology where the use of ionic beams provide an efficient and lowrisk contactless manipulation of the debris to be deorbited.
In order to prove the feasibility of the proposed solution and prepare for its future implementation a series of key milestones will be achieved:
(1) a detailed understanding of the physics underlining the concept,
(2) the identification of key technological challenges and concrete solutions
(3) the assessment of the concept capability in dealing with largescale removal operations
(4) the development of groundbased laboratory experiments,
(5) the definition of a clear technology and policy development roadmap,
(6) the prephase A design of a small technology demonstration mission and
(7) the exploitation and dissemination of the proposal outcomes.
A worldclass international team of universities and industrial partners from Europe and Ukraine has been formed in order to perform this study with a high level of theoretical and technical expertise in all relevant fields.
21/10/2013Director: Claudio Bombardelli //Participante: No Encontrado //Participante: Jesus Pelaez Alvarez//Participante: Juan Luis Gonzalo Gomez//Participante: No Encontrado //LNOVEL METHODOLOGY FOR GASSURFACE INTERACTIONS IN HYPERSONICS REENTRY FLOWSr"Novel methodology for gassurface interactions in hypersonic reentry flows" . The term "gassurface interactions" identifies the ensemble of the physical processes, typically superficial diffusion of mass, momentum, energy and chemical kinetics, that occur at the interfaces between a hightemperature gas mixture and the solid walls bounding the nonequilibrium hypersonic flow of the mixture. The unfortunately unexpected impossibility of implementation in available flow solvers pointed determines the necessity to develop novel numerical algorithms to deal with the novel form of the equations. This development line of research was initiated by TECMPA and that preliminary work lead to a positive assessment of CFD feasibility. Continuing along the same guidelines, the objective of this activity is the study of a twodimensional test case of more aerothermodynamic nature.GDirector: Jose Manuel Donoso Vargas//Participante: Pablo Solano Lpez//yOPTITRANS: Optimizacin del transporte de gas licuado en buques LNG mediante estudios sobre interaccin fluidoestructuraDirector: Leo Miguel Gonzalez Gutierrez//Participante: Daniel Duque Campayo//Participante: Antonio Souto Iglesias//Participante: Ricardo Zamora Rodriguez//Participante: Fabricio Macia Lang//Participante: Jesus Maria Gomez Goi//_PHYSICAL PROCESSES IN INERTIAL CONFINEMENT FUSION AND ALTERNATIVE IGNITION SCHEMES (EUROFUSIN)EURATOMLDirector: Fco. Javier Sanz Recio//Participante: Jose Javier Honrubia Checa//oPLASMAS ATMOSFRICOS PARA LA MEJORA DE LAS PROPIEDADES ADESIVAS Y SUPERFICIALES DE MATERIALES COMPUESTOS PAMPASDesarrollo de una antorcha de plasma atmosfrico para tratamiento de materiales metlicos y compuestos, mejorando las propiedades de adhesin.Aernnova Engineering SAUDirector: Luis Conde Lopez//Participante: Ezequiel Del Rio Fernandez//Participante: Jose Manuel Donoso Vargas//Participante: Juan Luis Domenech Garret//dPPICFAIS: Procesos Fsicos en Fusin por Confinamiento Inercial y Esquemas Alternativos de Ignicin
27/07/2015Participante: Jose Javier Honrubia Checa//Participante: Rafael Ramis Abril//Participante: Luis Felipe Ibaez Gonzalez//Director: Fco. Javier Sanz Recio//JSEHTOPQC: Aprovechamiento de Luz Solar mediante un proceso de dos fotones
16/12/2016GDirector: Perla Wahnon Benarroch//Codirector: Pablo Palacios Clemente//8Stardust: StardustThe Asteroid and Space Debris NetworkjAsteroids and space debris represent a significant hazard for space and terrestrial assets; at the same time asteroids represent also an opportunity. In recent years it has become clear that the increasing population of space debris could lead to catastrophic consequences in the near term. The Kessler syndrome (where the density of objects in orbit is high enough that collisions could set off a cascade) is more realistic than when it was first proposed in 1978. Although statistically less likely to occur, an asteroid impact would have devastating consequences for our planet. Although an impact with a large (~10 km) to medium (~300 m) sized, or diameter, asteroid is unlikely, still it is not negligible as the recent case of the asteroid Apophis has demonstrated. Furthermore impacts with smaller size objects, between 10 m to 100 m diameter, are expected to occur more frequently and hence are, proportionally, equally dangerous for humans and assets on Earth and in space. Asteroids and space debris share a number of commonalities: both are uncontrolled objects whose orbit is deeply affected by a number of perturbations, both have an irregular shape and an uncertain attitude motion, both are made of inhomogeneous materials that can respond unexpectedly to a deflection action, for both, accurate orbit determination is required, both need to be removed before they impact with something valuable for us.
The observation, manipulation and disposal of space debris and asteroids represent one of the most challenging goals for modern space technology. It represents a key scientific and commercial venture for the future in order to protect the space and Earth environment. Such a significant multidisciplinary technical challenge, with real societal benefit for the future, represents a compelling topic for a training network.
14/09/2012Participante: Davide Amato //Participante: Jesus Pelaez Alvarez//Participante: No Encontrado //Director: Claudio Bombardelli //BTEMPROCEN: NUEVAS TECNOLOGAS MATERIALES Y PROCESOS PARA EMPENAJESDesarrollo de una antorcha de plasma atmosfrico para tratamiento de materiales metlicos y compuestos, mejorando las propiedades de adhesin. LugarTipoFecha inicio Fecha finQEstancia de investigacin de Daniel Duque Campayo en la University of Washington.Estancia en la University of Washington, en colaboracin con el Prof. Michael Schick y su grupo. Nos proponemos centrarnos en el estudio de las membranas biolgicas. Se considerarn dos tipos de simulacin. 1. Hidrodinmica de membranas. 2. Hidrodinmica en membranas. Adems, nos proponemos establecer un vnculo de investigacin con el grupo receptor que permita iniciar una relacin de investigacin de ms larga duracin y que involucre a otros investigadores del centro de procedencia y del de acogida.
Por otro lado, se aprovechar la estancia para establecer contactos con otros grupos de la Universidad de Washington, incluyendo:
 El Departamento de Aeronutica William E Boing, en particular con el prof. Antonino Ferrante.
 El laboratorio de hidrulica Harris, del Departamento de Ingeniera Civil
 El grupo de Randa" J. leVeque, del Depto. de Matemtica Aplicada, autor principal del cdigo de simulacin Clawpack .Seattle, Washington, EEUU
01/09/2016
31/12/2016Autor: Daniel Duque Campayo//^Estancia de investigacin de Fernando Garca Rubio en la Universidad de Rochester, NY, EE.UU.Estancia en el Laboratory for Laser Energetics de la Universidad de Rochester bajo la tutela del Profesor Riccardo Betti. Proyecto de investigacin "Implosin de capsulas magnetizadas".
NY, EE.UU.
17/04/2016
20/08/2016Autor: Fernando Garcia Rubio//pEstancia de Investigacin de Javier Roa Vicens en Jet Propulsion Laboratory, California Institute of Technology.<Estudios de anlisis de misin en misiones interplanetarias.Caltech, Pasadena, USA
09/01/2016
30/09/2016Autor: Javier Roa Vicens//NEstancia de Investigacin de Javier Roa Vicens en la Universidad de Princeton.qNueva formulacin para estudiar la dinmica de un telescopio
espacial operando conjuntamente con un ocultador.
Princeton, NJ, USA
15/10/2016
17/11/2016WEstancia de investigacin de Javier Sanz Recio en Universidad de Rochester, NY, EE.UU.La estancia de colaboracin se enmarca dentro de las estancias previstas en la propuesta
del proyecto de investigacin ENE201454960R, del cual soy el investigador principal.
Es importante sealar que la colaboracin con este laboratorio (LLE, Rochester NY) se
lleva a cabo desde hace 20 aos de un modo estable y regular.
En concreto durante la estancia en Rochester de 4 semanas se completar el modelo
cilndrico de blanco magnetizado y el modelo de inestabilidad de RTI con campo
magntico autogenerado. Ambos modelos han sido ya iniciados en su estudio por mi
doctorando Fernando Garca Rubio que est realizando un< a estancia de 4 meses en dicho
laboratorio en colaboracin con el profesor de dicha institucin Ricardo Betti.
Rochester, NY
30/07/2016
28/08/2016Autor: Fco. Javier Sanz Recio//{Estancia de investigacin de Jorge Gonzlez Muoz en el Deutsche Zentrum fr Luft und Raumfahrt (DLR), Gttingen, AlemaniaEstacia en el Spacefraft Department bajo la tutela del Prof. Dr. Klaus Hannemann. Relacin con el proyecto: "Exploring angularmomentum phenomenology in aerothermodynamics and MHD"Gttingen, Alemania
01/02/2016
29/11/2016Autor: Jorge Gonzalez Muoz//[Estancia de investigacin de Rafael Ramis Abril en el MaxPlanckInstitut fuer Quantenoptik3Proyecto: ECEURATOM : eurofusion : ERWP15_CEA02Garching, Alemania
03/07/2016
24/07/2016Autor: Rafael Ramis Abril//QEstancia doctoral de Juan Luis Gonzalo Gmez en el Politcnico de Miln (Italia).Estancia doctoral en el Politcnico de Miln (Italia), bajo la supervisin del profesor Francesco Toputto (perteneciente al Departamento de Ciencia y Tecnologa Aeroespacial  Dipartamento di Scienze e Tecnologie Aeroespaziali). Dicha estancia tuvo lugar del 1 de Agosto al 15 de Noviembre de 2016 (3.5 meses).
Las actividades llevadas a cabo se centraron en la formulacin, implementacin y resolucin de problemas de optimizacin de trayectorias espaciales de bajo empuje en elementos orbitales modificados, formulados como Problemas de Control ptimo no lineales. Como caso de estudio se tom el diseo de maniobras de eliminacin al final de la vida til de satlites de navegacin en rbita Media Terrestre (constelacin Galileo). Los resultados de dicho estudio han sido muy satisfactorios: estn aceptados para su presentacin oral en un congreso internacional (26th ISSFD, 39 Junio 2017, Matsuyama, Japn), y se est preparando una publicacin en revista.
Adicionalmente, el doctorando asisti al profesor Topputo en la supervisin de un trabajo fin de mster basado parcialmente en el uso de las herramientas de control ptimo desarrolladas durante la estancia.Politcnico de Miln (Italia)
01/08/2016
15/11/2016 Autor: Juan Luis Gonzalo Gomez//ISBN
Tipo de TesisCalificacinFechaSAnalysis of wave resonant effects inbetween offshore vessels arranged sidebysideDoctoralSobresaliente cum laude
29/07/2016"Director: Jesus Maria Gomez Goi//Autor: Pasquale Dinoi UPM//lRegularization in Astrodynamics: applications to relative
motion, lowthrust missions, and orbit propagationh
Regularized formulations of orbital motion provide powerful tools for solving various problems in orbital
mechanics, both analytically and numerically. They rely on a collection of dynamical and mathematical
transformations that yields a more convenient description of the dynamics. The goal of the present thesis
is to recover the foundations of regularization, to advance the theory toward practical applications, and to
use this mathematical contrivance for solving three key challenges in modern astrodynamics: the dynamics
of spacecraft formations, the design of lowthrust trajectories, and the highperformance numerical propagation
of orbits.
The introduction of a fictitious time is a typical practice when regularizing the equations of motion.
This technique leads to a new theory of relative motion, called the theory of asynchronous relative motion.
It improves the accuracy of the linear propagation by introducing nonlinear terms through simple
dynamical mechanisms, and simplifies significantly the derivation of analytic solutions. In addition, it admits
any type of orbital perturbation. The method is compact and seems well suited for its implementation
in navigation filters and control laws. Universal and fully regular solutions to the relative dynamics follow
naturally from this theory. They are valid for any type of reference orbit (circular, elliptic, parabolic, or hyperbolic)
and are not affected by the typical singularities related to the eccentricity or inclination of the orbit.
The nonlinear corrections proposed by the method are generic and can be applied to existing solutions to
improve their accuracy without the need for a dedicated reimplementation.
We present a novel shapebased method for preliminary design of lowthrust trajectories: the family of
generalized logarithmic spirals. This new solution arises from the search for sets of orbital elements in the
accelerated case. It is fully analytic and involves two conservation laws (related to the equations of the energy
and angular momentum) that make the solution surprisingly similar to the Keplerian case and simplify the
design process. The properties of the solution to the Keplerian Lambert problem find direct analogues
in the continuousthrust case. An analysis of the dynamical symmetries in the problem shows that the
perturbing acceleration can be generalized and provides two additional families of analytic solutions: the
generalized cardioids and the generalized sinusoidal spirals.
As the complexity of space missions increases, more sophisticated orbit propagators are required. In
order to integrate flyby trajectories more efficiently, an improved propagation scheme is presented, exploiting
the geometry of Minkowski spacetime. The motion of the orbital plane is decoupled from the inplane
dynamics, and the introduction of hyperbolic geometry simplifies the description of the planar motion.
General considerations on the accuracy of the propagation of flyby trajectories are presented. In the context
of Nbody systems, we prove that regularization yields a simplified Lyapunovlike indicator that helps
in assessing the validity of the numerical integration. Classical concepts arising from stability theories are
extended to higher dimensions to comply with the regularized statespace. In this thesis, we present, for the
first time, the gaugegeneralized form of some elementbased regularized formulations.:Autor: Javier Roa Vicens//Director: Jesus Pelaez Alvarez//JCR del ISITtulo de la revistaISSNFactor de impacto JCRInformacin de impactoVolumenDOINmero de revistaDesde la pginaHasta la pginaMesRanking@ Analytic method for sputtering yield calculation in nanoislands%Se calcula el sputtering de nanoislasChemical Physics Letters 000926141,86Datos JCR del ao 2015664226232SIN MES!Autor: Jose Carlos Jimenez Saez//CAutor: A.M.C. Prez Martn UCM//Autor: J.J. Jimnez Rodrguez UCM//VAPPROXIMATE ANALYTICAL SOLUTION OF THE MULTIPLE REVOLUTION LAMBERT'S TARGETING PROBLEM$SPACEFLIGHT MECHANICS 2016, PTS IIV 108160031581471607Autor: Claudio Bombardelli //Autor: Javier Roa Vicens//Autor: juan luis gonzalo //\Approximate Solution of Nonlinear Circular Orbit Relative Motion in Curvilinear CoordinatesGSolucin al problema del movimiento relativo en coordenadas curvilneas)Celestial Mechanics & Dynamical Astronomy 092329582,084Datos JCR del ao 201310.1007/s105690169716x18WAutor: Claudio Bombardelli //Autor: Juan Luis Gonzalo Gomez//Autor: Javier Roa Vicens//MCOMPACT SOLUTION OF CIRCULAR ORBIT RELATIVE MOTION IN CURVILINEAR COORDINATESASTRODYNAMICS 2015156925935dComparison between experimental Langmuir probes and three species onedimensional kinetic simulationsgThe biasing of Langmuir probes to obtain the appropriate measurements in weakly ionized plasmas
is addressed in this work. The experimental results show discrepancies when this measurement
method is employed with sweep signals of different symmetries or frequencies. This means that the
method provides signal dependent plasma parameters, which hinder its diagnosis. In this work, a
three species onedimensional kinetic model is applied with a sweep electric field to simulate the
dynamics of a weakly ionized plasma close to a Langmuir probe. With the same symmetries and
frequencies for the sweep signal in both the experimental and numerical problems, a qualitative
similar behaviour is found. The response of the three species plasma due to changes of the electric
field is analysed by means of a three species kinetic collisional model. The effect of constant ave< raged
or energy dependent characteristic collision frequencies is studied. These numerical results
are useful to provide a first explanation of the discrepancies found in the experimental data and
improve the measurement process. Published by AIP Publishing.Physics of Plasmas 1070664X2,2492310.1063/1.496542510351411035147OCTUBRE?Autor: Jorge Gonzalez Muoz//Autor: Jose Manuel Donoso Vargas//Autor: S. P: Tierno UCV//(CONTACTLESS ION BEAM ASTEROID DESPINNING383938525Autor: Claudio Bombardelli //Autor: No Encontrado //Autor: daniel pastormoreno //ZDiagnostic of plasma streams from ion thrusters for space propulsion using emissive probesThe diagnostic
using emissive probes is reviewed with emphasis in low density plasmas. Our results support the
conclusion that potential structures around the probe, as virtual cathodes, would be responsible
for the operation of emissive probes in low density plasmas.
1.& Journal of Physics: Conference Series
ISSN 174265880,211SJR H Index 76810.1088/17426596/768/1/01201001201010120107Autor: Luis Conde Lopez//Autor: Sandra Pilar Tierno Gomez//Autor: Juan Luis Domenech Garret//Autor: Jose Manuel Donoso Vargas//Autor: M. A. Castillo Aernnova Engineering Solutions//Autor: I. Eiriz Centro de Tecnologas Aeronauticas, Mi~nano, Vitoria//Autor: I, Saez de Ocariz Centro de Tecnologas Aeronauticas, Minano, Vitoria//DROMO propagator revisited)CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY1,612410.1007/s105690159647y31RAutor: No Encontrado //Autor: Jesus Pelaez Alvarez//Autor: Manuel Sanjurjo Rivo//AEFFICIENT TRAJECTORY PROPAGATION FOR ORBIT DETERMINATION PROBLEMS3613807Autor: Javier Roa Vicens//Autor: Jesus Pelaez Alvarez//;Electronic band alignment at CuGaS2 chalcopyrite interfacesCuchalcopyrite semiconductors are commonly used as light absorbing materials on solar cell devices. The study of the heterointerfaces between the absorbent and the contact materials is crucial to understand their operation. In this study, band alignments of the heterojunctions between CuGaS2 chalcopyrite and different semiconductors have been theoretically obtained using density functional theory and more advanced techniques. Band alignments have been determined using the average electrostatic potential as reference level. We have found that the strain in the heterointerfaces plays an important role in the electronic properties of the semiconductors employed here. In this work CuAlSe2/CuGaS2 and CuGaS2/ZnSe heterointerfaces show band alignments where holes and electrons are selectively transferred through the respective heterojunctions to the external contacts. This condition is necessary for their application on photovoltaic devices.Computational Materials Science 092702561,87912110.1016/j.commatsci.2016.04.0327985?Autor: Pablo Palacios Clemente//Autor: Perla Wahnon Benarroch//JAutor: J.E. Castellanos Aguila //Autor: J.C. Conesa //Autor: J. Arriaga //JEnhancement of fast electron energy deposition by external magnetic fieldsU8TH INTERNATIONAL CONFERENCE ON INERTIAL FUSION SCIENCES AND APPLICATIONS (IFSA 2013) 1742658868810.1088/17426596/688/1/0120334#Autor: Jose Javier Honrubia Checa//Autor: m. murakami //Autor: k. mima //Autor: t. johzaki //Autor: a. sunahara //Autor: h. nagatomo //Autor: s. fujioka //Autor: h. shiraga //Autor: h. azechi //fEvaluation of the statistical properties for typeII intermittency using the PerronFrobenius operatorNONLINEAR DYNAMICS 0924090X2,8498610.1007/s1107101629516211071116#Autor: Ezequiel Del Rio Fernandez//0Autor: sergio elaskar //Autor: eduardo zapico //`Existence of a virtual cathode close to a strongly electron emissive wall in low density plasmasThe interaction between an electron emissive wall, electrically biased in a plasma,
is revisited through a simple fluid model. We search for realistic conditions of the
existence of a nonmonotonic plasma potential profile with a virtual cathode as it
is observed in several experiments. We mainly focus our attention on thermionic
emission related to the operation of emissive probes for plasma diagnostics, although
most conclusions also apply to other electron emission processes. An extended Bohm
criterion is derived involving the ratio between the two different electron densities at
the potential minimum and at the background plasma. The model allows a phase
diagram analysis, which confirms the existence of the nonmonotonic potential profiles
with a virtual cathode. This analysis shows that the formation of the potential well
critically depends on the emitted electron current and on the velocity at the sheath
edge of cold ions flowing from the bulk plasma. As a consequence, a threshold value
of the governing parameter is required, in accordance to the physical nature of the
electron emission process. This latter is a threshold wall temperature in the case
of thermionic electrons. Experimental evidence supports our numerical calculations
of this threshold temperature. Besides this, the potential well becomes deeper with
increasing electron emission, retaining a fraction of the released current which limits
the extent of the bulk plasma perturbation. This noninvasive property would explain
the reliable measurements of plasma potential by using the floating potential method
of emissive probes operating in the socalled strong emission regime.10.1063/1.4939042013503013510ENEROAutor: Sandra Pilar Tierno Gomez//Autor: Jose Manuel Donoso Vargas//Autor: Juan Luis Domenech Garret//Autor: Luis Conde Lopez//@GENERALIZED LOGARITHMIC SPIRALS FOR LOWTHRUST TRAJECTORY DESIGN29772996Generation and characterization of warm dense matter isochorically heated by laserinduced relativistic electrons in a wire targetEPL 029550752,09511410.1209/02955075/114/4500263Autor: a. schoenlein //Autor: g. boutoux //Autor: s. pikuz //Autor: l. antonelli //Autor: d. batani //Autor: a. debayle //Autor: a. franz //Autor: l. giuffrida //Autor: j. jacoby //Autor: d. khaghani //Autor: p. neumayer //Autor: o. n. rosmej //Autor: t. sakaki //Autor: j. j. santos //Autor: a. sauteray //(GTOC8: RESULTS AND METHODS OF POLIMIUPM43014308Autor: Claudio Bombardelli //<Autor: francesco topputo //Autor: diogene a. dei tos //Autor: daniele filippetto //Autor: aureliano rivolta //Autor: mauro massari //Autor: amedeo rocchi //Autor: pierluigi di lizia //Autor: hodei urrutxua //Autor: vincenzo pesce //Autor: andrea colagrossi //Autor: juan luis gonzalo //Autor: daniel pastor moreno //ZIMPACT OF THE INTEGRATION STOPCONDITION ON THE ACCURACY OF REGULARIZED ORBIT FORMULATIONS250325165Autor: No Encontrado //Autor: Jesus Pelaez Alvarez//Autor: claudio bornbardelli //RIntegral propagator method as a kinetic operator to describe discontinuous plasmashe usual numerical schemes based on differences may fail to represent these abrupt conditions by inducing numerical viscosities and instabilities. However, the robust meslifree computational integral method has been proved to be unconditionally stable in the simple case of no imposed restrictions by boundary conditions. The extension of the method to deal with boundary value problems is analysed. The advancing scheme is also useful to deal with the merging of natural discontinuities in the system as those induced by the effects of electromagnetic fields generated by charge separation as well as for the existence of two differentiated plasma regimes. In any case, the kinetic equation may have drift and/or diffusion coefficients that are likewise discontinuous. The scheme works as an effective integral kinetic operator even for FokkerPlanck equations connecting two different dynamical statistics, like MaxwellBolt.zmann and Fermi Dirac ones. %Journal of Physics: Conference SeriesSJR H Index10.1088/17426596/768/1/01200401200410120049 NOVIEMBREXAutor: Jose Manuel Donoso Vargas//Autor: Jorge Gonzalez Muoz//Autor: Luis Conde Lopez//Autor: A. Jimenez HIdalgo upm//TIntense laser driven collisionless shoc< k and ion acceleration in magnetized plasmasThe generation of strong magnetic field with a laser driven coil has been demonstrated by many experiments. It is applicable to the magnetized fast ignition (MFI), the collisionless shock in the astrophysics and the ion shock acceleration. In this paper, the longitudinal magnetic field effect on the shock wave driven by the radiation pressure of an intense short pulse laser is investigated by theory and simulations. The transition of a laminar shock (electro static shock) to the turbulent shock (electromagnetic shock) occurs, when the external magnetic field is applied in near relativistic cutoff density plasmas. This transition leads to the enhancement of conversion of the laser energy into high energy ions. The enhancement of the conversion efficiency is important for the ion driven fast ignition and the laser driven neutron source. It is found that the total number of ions reflected by the shock increases by six time when the magnetic field is applied.BAutor: Fco. Javier Sanz Recio//Autor: Jose Javier Honrubia Checa//XAutor: K. Mima //Autor: Q Jia //Autor: H B Cai //Autor: T Taguchi //Autor: H Nagatomo //PINTRODUCING A DEGREE OF FREEDOM IN THE FAMILY OF GENERALIZED LOGARITHMIC SPIRALS299318UMagnetized Fast ignition (MFI) and Laser Plasma Interactions in Strong Magnetic Field10.1088/17426596/688/1/012066Autor: kunioki mima //Autor: t. johzaki //Autor: h. nagatomo //Autor: t. taguchi //Autor: a. sunahara //Autor: h. sakagami //Autor: s. fujioka //Autor: g. logan //LMission analysis for the ion beam deflection of fictitious asteroid 2015 PDCACTA ASTRONAUTICA 009457651,12211810.1016/j.actaastro.2015.11.003296307Autor: Davide Amato //8Autor: claudio bombardelli UPM//Autor: juan luis cano //{Modeling of thermal effect on the electronic properties of photovoltaic perovskite CH3NH3PbI3: the case of tetragonal phaseHybrid organicinorganic perovskites are semiconductors with disordered structures and remarkable properties for photovoltaic applications. Many theoretical investigations have attempted to obtain structural models of the hightemperature phases, but most of them are focused on the mobility of organic components and their implications in material properties. Herein we propose a set of geometric variables to evaluate the conformation of the inorganic framework at each phase of methylammonium lead iodide perovskite. We show that the analysis of these variables is required to ensure consistent structural models of the tetragonal phase. We explore the theoretical ingredients needed to achieve good models of this phase. Ab initio molecular dynamic simulation, under canonical ensemble at the experimental unit cell volume, leads to representative states of the phase. Under this scheme, PBE and van der Waals density functional approaches provide similar models of the tetragonal phase. We find that this perovskite has a highly mobile inorganic framework due to the thermal effect regardless of movement of the organic cations. Consequently, the electronic structure shows significant movements of the bands with large bandgap variations.Journal of Physical Chemistry C 193274474,83512010.1021/acs.jpcc.6b010131579767986hAutor: A.L. MonteroAlejo //Autor: E. MenndezProupin //Autor: D. HidalgoRojas //Autor: J.C. Conesa //]MULTIIFEA onedimensional computer code for Inertial Fusion Energy (IFE) target simulationsCOMPUTER PHYSICS COMMUNICATIONS 001046553,11220310.1016/j.cpc.2016.02.014237Autor: j. meyertervehn //MNew Analytic Solution with Continuous Thrust: Generalized Logarithmic Spirals(JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 073150901,2913910.2514/1.G0003411023362351Autor: juan senent //VNonconservative extension of Keplerian integrals and a new class of integrable system1MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY 003587115,10746310.1093/mnras/stw2209332043219?On intense proton beam generation and transport in hollow conesProton generation, transport and interaction with hollow cone targets are investigated by means of twodimensional PIC simulations. A
scaleddown hollow cone with gold walls, a carbon tip and a curved hydrogen foil inside the cone has been considered. Proton acceleration is
driven by a 1020 W$cm?2 and 1 ps laser pulse focused on the hydrogen foil. Simulations show an important surface current at the cone walls
which generates a magnetic field. This magnetic field is dragged by the quasineutral plasma formed by fast protons and comoving electrons
when they propagate towards the cone tip. As a result, a tens of kT Bz field is set up at the cone tip, which is strong enough to deflect the protons
and increase the beam divergence substantially. We propose using heavy materials at the cone tip and increasing the laser intensity in order to
mitigate magnetic field generation and proton beam divergence.!Matter and Radiation at Extremes 2468204736Autor: A. Morace Institute of Laser Engineering, Osaka University, Osaka, Japan//Autor: M. Murakami Institute of Laser Engineering, Osaka University, Osaka, Japan//)On the Theory of Intermittency in 1D Maps.INTERNATIONAL JOURNAL OF BIFURCATION AND CHAOS 021812741,0782610.1142/S021812741650228X1411Autor: sergio elaskar //>OPTIMAL LOW THRUST ORBIT CORRECTION IN CURVILINEAR COORDINATES19411958Autor: juan l. gonzalo //7OPTIMAL 3D ORBIT CORRECTIONS IN CURVILINEAR COORDINATES397414LPairs of Subsets of Regular Polyhedra with the Same Distribution of DistanceSe explica un ejemplo de Mallows y Clark de 1970 de un par de dodecgonos no congruentes pero con la misma distribucin de distancia. Este entendimiento permite construir infinitos pares de polgonos con la misma propiedad que se construyen a partir de polgonos regulares. Finalmente, se avanzan algunas conjeturas sobre el mismo fenmeno en un mayor nmero de dimensiones que se confirman en una publicacin posterior.Applied Mathematical Sciences 1312885X0,6310.12988/ams.2016.639612851297)Autor: Ricardo Angel GarciaPelayo Novo//SPlasma expansion into a vacuum with an arbitrarily oriented external magnetic fieldPHYSICS OF PLASMAS2,14210.1063/1.4939476ZAutor: Fernando Garcia Rubio//Autor: Jose Luis Muoz Sanz//Autor: Fco. Javier Sanz Recio//Autor: a. ruocco //oProposals for improving evaluation systems in higher education: An approach from the model'Working with People'+Journal of Technology and Science Education 20136374Indexada en Scopus10.3926/jotse.192104#Autor: Consuelo Fernandez Jimenez//Autor: Ignacio de los Ros UPM//Autor: Susana Sastre Merino UPM//Autor: Cristina Nuez UPM//Autor: Encarnacin Reyes UPM//Autor: Noemi GarcaArjona UPM//@QUANTIFICATION OF THE PERFORMANCE OF NUMERICAL ORBIT PROPAGATORS24852501lAutor: No Encontrado //Autor: Claudio Bombardelli //Autor: Javier Roa Vicens//Autor: Jesus Pelaez Alvarez//AScience for Everybody: A Proposal for Fostering Learning from OCW/The International Journal of Science in Society 183662368%http://doi.org/10.18848/18366236/CGP25MARZOfAutor: Consuelo Fernandez Jimenez//Autor: Maria Laura Hernando Guadao//Autor: Federico Prieto Muoz//9Series for Collision Probability in ShortEncounter Model10.2514/1.G00175419041912Autor: javier hernandoayuso //Spiral Lambert's Problem10.2514/1.G00034222502263=SPIRAL LAMBERT'S PROBLEM WITH GENERALIZED LOGARITHMIC SPIRALS279298OStability and chaos in KustaanheimoStiefel space induced by the Hopf fibration45910.1093/mnras/stw78024442454OAutor: Javier Roa Vicens//Autor: No Encontrado //Autor: Jesus Pelaez Alvarez//PSurvivability analysis of tapetether against two concurring impacts with debrisADVANCES IN SPACE RESEARCH 027311771,3585710.1016/j.asr.2016.03.01822732284YAutor: Ricardo Angel GarciaPelayo Novo//Autor: No Encontrado //Autor: No Encontrado //AThe spectrum of the SedovTaylor point explosion linear stability10.1063/1.495342421<A< utor: Jose Luis Muoz Sanz//Autor: Fco. Javier Sanz Recio//?Autor: s. e. bouquet //Autor: c. michaut //Autor: j. miniere //MThermodynamic properties of thermonuclear fuel in inertial confinement fusionLASER AND PARTICLE BEAMS 026303461,2953410.1017/S0263034616000422539544<Autor: v. brandon //Autor: b. canaud //Autor: m. temporal //FThree species onedimensional kinetic model for weakly ionized plasmas10.1063/1.49539019Autor: s. p. tierno //1THREEDIMENSIONAL GENERALIZED LOGARITHMIC SPIRALS319338LThreedimensional singlemode nonlinear ablative RayleighTaylor instability10.1063/1.4940917VAutor: r. yan //Autor: r. betti //Autor: h. aluie //Autor: b. liu //Autor: a. frank //Edicin del LibroEditorial del LibroSerieTtulo del LibroDesde pginaHasta pginaVAdvanced orbit propagation methods and application to space debris collision avoidanceThe nature of numerical error is explained at the beginning of the chapter by separating it into local truncation and roundoff error components. Advanced orbit propagation methods that based on regularizing and linearizing the equations of motion are described. One of these methods, based on regularized equations of motion for nonclassical orbital elements, is applied to an analytical application for purposes of collision avoidance.!10.2514/5.9781624103247.0049.0070CAmerican Institute of Aeronautics and Astronautics, Reston, VA, USA
9781624103230(Progress in Astronautics and AeronauticsSAsteroid and Space Debris Manipulation: Advances from the Stardust Research Network49703Autor: Davide Amato //Autor: Claudio Bombardelli //#Orbital Dynamics About Small BodiesIn recent years, knowledge of NearEarth Asteroids (NEAs) and missions to small bodies in the Solar System have enjoyed a considerable activity. The dynamical environment in the vicinity of small Solar System bodies is outlined, emphasizing the main perturbations acting on a spacecraft in a highly perturbed orbit. The dynamical requirements for orbital stability around asteroids are outlined through an analytical, averaged method.10.2514/5.9781624103151162&Autor: Juan Luis Cano Elecnor Deimos//ISSN o ISBNEntidad relacionadaLugar del congresoTPlasma Expansion into a Vacuum with an Arbitrarily Oriented External Magnetic Field.Se estudia la expansin libre al vaco de un plasma magnetizado externamente. La solucin presenta una estructura autosemejante y depende de dos parmetros que gobiernan el problema son inclinacin inicial en el campo magntico y el ratio de presiones trmica y magntica.
00030503o36th International Workshop on High Density Energy Physics
with Intense Ion and Laser Beams.
Hirschegg, Austria=Autor: Fernando Garcia Rubio//Autor: Fco. Javier Sanz Recio//=Proton driven fast ignition: Current status and perspectives O3rd International Conference on High Energy Density Physics, Sep 23rd?26th 2016Shenzhen, China./Proton fast ignition of inertial fusion targetsC1st Conference on Matter and Radiation at Extremes  May 812, 2016Chengdu, China.Proton fast ignition revisitedn14th International Workshop on Fast Ignition & High Field Physics with High Power Lasers, May 17th?20th 2016, Yokohama, JapnNombre congresoEntidad organizadoraLugar/Ciudad de imparticin&Metodologa y Documentacin CientficaAActividad formativa como parte del doctorado, con 20h de duracinETSIAE, Madrid
09/03/2016
30/05/2016Autor: Virginia Raposo Pulido//EntidadPginasReferencia/URLTipo de publicacin&Upgrade of the hydrodynamic code MULTIKHEDgeHOB Collaboration at FAIR  Report 2015
GSI20162 REPORT (June 2016)
%Contribucin al Report de laboratorioAutor: F.Y. Wu //Tipo de participacin RevisoresISBN o ISSNFecha inicio congresoFecha fin congresoTtulo de las actas=Advanced special perturbations for asteroids and space debrisWe present new special perturbations methods for the accurate and efficient propagation of interplanetary and geocentric dynamics. The methods are based on the integration of regularized equations of motion with adaptive numerical solvers. We apply our approach to the propagation of planetary close encounters and of orbits in the MEO/GEO regions. For planetary encounters, it is possible to gain up to two orders of magnitude in accuracy with respect to the integration of the equations of motion in Cartesian coordinates at half of the computational cost. Also, integrations of nonaveraged regularized equations may exhibit equal or lower computational times for geocentric propagations when compared to semianalytical methods.Stardust Final Conference960Noordwijk, Paises Bajos
31/10/2016
04/11/20163Autor: Claudio Bombardelli //Autor: Davide Amato //4Autor: Giulio Ba Universit di Pisa, Pisa, Italia//QAn efficient code to solve the Kepler equation for elliptic and hyperbolic orbits
The Kepler equation for the elliptical motion, y ? e sin y ? x = 0, involves a nonlinear function depending on three parameters: the eccentric anomaly y = E, the eccentricity e and the mean anomaly x = M. For given e and x values the numerical solution of the Kepler equation becomes one of the goals of orbit propagation to provide the position of the object orbiting around a body for some specific time. In this paper, a new approach for solving Kepler equation for elliptical and hyperbolic orbits is developed. This new approach takes advantage of the very good behavior of the Laguerre method when the initial seed is close to the looked for solution and also of the existence of symbolic manipulators which facilitates the obtention of polynomial approximations. The central idea is to provide an initial seed as good as we can to the modified NewtonRaphson method, because when the initial guess is close to the solution, the algorithm is fast, reliable and very stable. To determine a good initial seed the domain of the equation is discretized in several intervals and for each one of these intervals a fifth degree interpolating polynomial is introduced. The six coefficients of the polynomial are obtained by requiring six conditions at both ends of the corresponding interval. Thus the real function and the polynomial have equal values at both ends of the interval. Similarly relations are imposed for the two first derivatives. Consequently, given e and x = M, selecting the interval [xi, xi+1] in such a way that M belongs to [xi, xi+1] and using the corresponding polynomial pi(x), we determine the starter value y0 = E0. However, the Kepler equation has a singular behavior when M is small and e close to unity (singular corner). In this case, the exact solution of the equation has to be described in a different way to guarantee the enough accuracy to be part of the seed used to start the numerical method. In order to do that, an asymptotic expansion in power of the small parameter ? = 1?e is developed. In most of the cases, the seed generated by the Space Dynamics Group at UPM (SDGcode) leads to reach machine error accuracy with the modified NewtonRaphson methods with no iterations or just one iteration. The final algorithm is very stable and reliable. This approach improves the computational time compared with other methods currently in use. The advantage of our approach is its applicability to other problems as for example the Lambert problem for low thrust trajectories. A method solving Kepler?s equation without transcendental function evaluations.NICATT2016: 6th International Conference on Astrodynamics Tools and Techniques Darmstadt (Germany)
14/03/2016
17/03/2016<Autor: Virginia Raposo Pulido//Autor: Jesus Pelaez Alvarez//LApproximate Analytical Solution of the Multiple Revolution Lambert?s ProblemAn approximate analytical solution of the multiple revolution Lambert?s targeting problem is presented. The solution is obtained starting from Battin?s optimum singleimpulse transfer with a linear phasing correction and offers remarkable accuracy near minimum deltaV transfer conditions. Consequently, the method is useful for rapidly obtaining low deltaV s< olutions for interplanetary trajectory optimization. The solution is easy to program and noniterative, which makes it ideal for GPU implementation. In addition, the method can be employed to provide a fast first guess solution for enhancing the convergence speed of an accurate numerical multirevolution Lambert solver.+26th AAS/AIAA Spaceflight Mechanics MeetingNapa, California
14/02/2016
18/02/2016&Advances in the Astronautical SciencesWAutor: Claudio Bombardelli //Autor: Javier Roa Vicens//Autor: Juan Luis Gonzalo Gomez//^Efficient numerical propagation of planetary close encounters with regularized element methodsXClose encounters with major Solar System bodies may bring about a strong amplification of numerical error during interplanetary orbit propagation. In this work, we reduce global numerical error by integrating regularized equations of motion instead of the classical Newtonian equations in Cartesian coordinates. The integration performance of several sets of
regularized equations is assessed from largescale numerical propagations of close encounters in the SunEarth planar CR3BP. An essential device is switching between primary bodies during the propagation, which effectively decomposes a stronglyperturbed heliocentric problem into two weaklyperturbed ones; this propagation approach has been dubbed Online Trajectory Matching (OTM). Through this simple expedient, regularized equations describing the evolution of nonclassical orbital elements achieve excellent performances compared to Newtonian equations, even when employing sophisticated adaptive numerical schemes. Further improvements might be expected by carefully selecting the location of the switch of primary bodies during the propagation.
J6th International Conference on Astrodynamics Tools and Techniques (ICATT)Darmstadt, AlemanianPublicacin en linea: https://indico.esa.int/indico/event/111/session/16/contribution/149/material/paper/0.pdfJEfficient special perturbation techniques for orbital lifetime predictions
Efficiency in the propagation of a large number of initial conditions over long time spans drives the requirements for space debris orbit propagation techniques. This need arises quite naturally in the simulation of large debris populations for evolutionary studies, but also longterm orbital lifetime predictions often need massive propagations to draw physically meaningful conclusions. For instance, a Monte Carlo approach is mandatory to make up for uncertainties in the physical characteristics of the atmosphere and spacecraft, or to sample a limited space of initial conditions when chaotic dynamics in longterm propagations are known to ensue.
Analytical and semianalytical methods offer reasonable accuracy for a low computational cost when all the main dynamical phenomena occurring in a specific problem are correctly taken into account. Yet, if knowledge of the underlying dynamics might be incomplete or for purposes of verification of these methods in challenging scenarios one must resort to a special perturbations method. Such a method has to be accurate enough to generate reliable reference solutions, and to provide them in a reasonable time.
Integrations of the equations of motion of a set of nonsingular orbital elements have already shown superior efficiency compared to those performed in Cartesian coordinates, besides lightening the burden on numerical integration schemes. The Dromo family of regularized element methods, based on a special perturbations method originally developed for the propagation of space tethers [1], has excelled in these aspects in a variety of test cases [2].
In this work, firstly we expand the applicability of the Dromo methods by describing the implementation of a physical model with an mbyn gravitational potential and atmospheric drag from a timedependent atmosphere.
Furthermore, we assess the performance of these methods compared with the direct integration of the Newtonian equations and with available semianalytical codes. The comparison is done by using the aforementioned physical model in the propagation of test cases representative of HEO and MEO orbits. For the direct numerical integrations, we employ a multistep integrator with variable step size and order which uses the AdamsBashforthMoulton numerical scheme and backwards differences formulas [3]. In order to measure the accuracy of the methods, we compute the error in the estimated lifetime with respect to a reference solution and we compare the calculated trajectories with those obtained from processing historical TLE data of real objects.
'Second Stardust Global Virtual Workshop?University of Southampton, Southampton, Inglaterra, Reino Unido
19/01/2016
22/01/2016(GTOC8: Results and Methods of PoliMiUPMJIn this work the solution to the 8th Global Trajectory Optimization Competition proposed from the PoliMiUPM team is presented. With the aim of maximizing the objective function, a twostage strategy has been devised. First, two spacecraft target selenoflybys to significantly modify their orbital parameters, in particular increasing the semimajor axis. Later, the formation is steered with lowthrust propulsion to point radio sources within the assigned tolerance. The latter is achieved by means of a geometrical method that minimizes the orbital parameters variation, and that provides boundary condition for an indirect method solution of the Twopoint Boundary Value Problem. No constraints on the number of seen radio sources have been applied. On a higher level, a genetic algorithm is used to identify the optimal flyby parameters.,26th AAS/AIAA Space Flight Mechanics MeetingNapa, California (EEUU)MAdvances in the Astronautical Sciences Volume 158, Spaceflight Mechanics 2016UAutor: Juan Luis Gonzalo Gomez//Autor: Claudio Bombardelli //Autor: No Encontrado //Autor: Francesco Topputo Politecnico di Milano//Autor: Diogene A. Dei Tos Politecnico di Milano//Autor: Daniele Filippetto Politecnico di Milano//Autor: Aureliano Rivolta Politecnico di Milano//Autor: Mauro Massari Politecnico di Milano//Autor: Amedeo Rocchi Politecnico di Milano//Autor: Pierluigi Di Lizia Politecnico di Milano//Autor: Hodei Urrutxua University of Southampton//Autor: Vincenzo Pesce Politecnico di Milano//Autor: Andrea Colagrossi Politecnico di Milano//OHot spot model of MagLIF implosions: Nernst term effect on magnetic flux lossesAn analytical model of a collisional plasma being compressed by a cylindrical liner is proposed and solved in a magnetized liner inertial fusionlike context. The implosion is assumed to be isobaric, and the magnetic diffusion is confined to a thin layer near the liner. Both unmagnetized and magnetized plasma cases are considered. The model reduces to a system of two partial differential equations for temperature and magnetic field. Special attention is given to the effect of the Nernst term on the evolution of the magnetic field. Scaling laws for temperature, magnetic field, hot spot mass increase and magnetic field losses are obtained. The temperature and magnetic field spatial profiles tend to a selfsimilar state. It is found that when the Nernst term is taken into account, the magnetic field is advected towards the liner, and the magnetic flux losses are independent of the magnetic Lewis number.
958th Annual Meeting of the APS Division of Plasma PhysicsSan Jose, CA+APS Division of Plasma Physics Meeting 2016Autor: Riccardo Betti //ZImpact of the Integration StopCondition on the Accuracy of Regularized Orbit FormulationsThe tight relationship between the stopcondition of a numerical integrator and the resulting accuracy of regularized orbit propagators is addressed. It is noted that the use of events as a means to halt the numerical orbit propagation introduces timing or phasing errors in formulations involving a Sundman transformation. The fundamentals of this timing error are described, along with the mechanisms that produce this apparent loss in the achievable accuracy. This behavior is linked to the dynamical instabilities of the orbital motion. Examples are provided to support that the purely geometrical descr< iption provided by regularized methods is typically orders of magnitude more accurate than when the timing error is taken into account.:Autor: Claudio Bombardelli //Autor: Jesus Pelaez Alvarez//2Autor: Hodei Urrutxua University of Southampton//PIntroducing a degree of freedom in the family of generalized logarithmic spiralsThe versatility of the family of generalized logarithmic spirals is improved by introducing a degree of freedom in the solution. The lowthrust acceleration profile now includes a control term that affects both the magnitude and the direction of the thrust. Exact and fully analytic solutions to the trajectory, the velocity, the time of flight, etc. are made available. Two integrals of motion are preserved. The first one is a generalization of the equation of the energy and depends on the values of the control parameter. The second one relates to the equation of the angular momentum. The problem of finding spiral transfers between two arbitrary state vectors reduces to solving one algebraic equation with one unknown. The degree of freedom allows fixing the time of flight of the transfer. If the time of flight is fixed, then there are two equations with two unknowns. No other iterative procedures are required. Coast arcs can be introduced in the solution naturally. An explicit expression for the maximum acceleration reached along the transfer is provided. Thanks to the symmetry properties of the solution a simple algorithm for generating periodic orbits is presented. An arbitrary number of intermediate nodes can be introduced to improve the flexibility of the solution when facing optimization problems. An example of a lowthrust gravityassist EarthMarsCeres trajectory shows that the solution is comparable to that obtained with other preliminary design techniques."26th Spaceflight Mechanics Meeting20LMultiple Revolution Lambert's Targeting Problem: An Analytical Approximation=Solving a Lambert's Targeting Problem (LTP) consists of obtaining the minimum required singleimpulse deltaV to modify the trajectory of a spacecraft in order to transfer it to a selected orbital position in a fixed time of flight. We present an approximate analytical method for rapidly solving a generic LTP with limited loss of accuracy. The solution is built on an optimum singleimpulse timefree transfer with a Dmatrix phasing correction. Because it exhibits good accuracy (both in terms of deltaV and time of flight) near locally optimum transfer conditions the method is useful for rapidly obtaining low deltaV solutions for interplanetary trajectory optimization. In addition, the method can be employed to provide a first guess solution for enhancing the convergence speed of an accurate numerical Lambert solver.
ANew orbital elements for accurate propagation in the Solar SystemIn this paper we present new variables to describe the orbital motion of a celestial body in the Solar System. The motion is the solution of a perturbed twobody problem, where the main perturber can be the Sun or any planet. Two sets of generalized orbital elements are proposed for positive and negative values of the total energy, respectively. The former is the subject of the paper [1], while the latter is here presented for the first time. Numerical tests for perturbed geocentric motion and close encounters with a planet show that the new coordinates are very efficient when compared with both regularized and Cowell?s methods.pPublicacin en linea:
https://indico.esa.int/indico/event/111/session/30/contribution/111/material/slides/0.pdf
kAutor: Giulio Ba Universit di Pisa, Pisa, Italia//Autor: Andrea Milani Universit di Pisa, Pisa, Italia//LNon equilibrium thermal and electrical transport coefficients for hot metals/This work is focused on the discussion about the transport coefficients for non equilibrium hot metals. First, we review the role of the non equilibrium Kappa distribution, [1], in which The Kappa parameter varies with the temperature [1, 2]. A brief discussion compares such distribution with the classical non equilibrium function used in metals. Later, we show the derivation of the generalized electrical conductivity [3]. Also, it is shown the connection between the melting point of the metal and a materialdependent coefficient which can be extracted by analyzing its thermionic emission[3]. We extend previous studies by analyzing additional metals used as thermionic emitters. Finally, in the light of the WiedemannFranz Law, we present a new generalized thermal conductivity, which is also analyzed.611th International Workshop on Subsecond ThermophysicsKrakow, Poland9788394490225
21/06/2016
24/06/201691Procceeding 11th International Workshop on Subsecond Thermophysics, Editors: N.Sobczak, T.Dudziak,
Publisher: Foundry Research Institute (Instytut OdlewnictwaPoland).
;Autor: Juan Luis Domenech Garret//Autor: Luis Conde Lopez//cNumerical Simulation of the Interaction Between Z Pinch Plasma and Foam Converter Using Code MULTI C22nd Topical Meeting on the Technology of Fusion Energy PhiladelfiaPhiladelphia, PA
22/08/2017
25/08/2016$Autor: Fuyuan Wu //Autor: et. al. //;OCCAM: Optimal Computation of Collision Avoidance ManeuversIOCCAM (Optimal Computation of Collision Avoidance Maneuvers) is a novel software tool aimed at computing minimumfuel collision avoidance maneuvers in the shortterm encounter scenario, which is generally applicable in LEO. Developed by the Space Dynamics Group of the Technical University of Madrid, it employs advanced modeling and optimization techniques, which make it an extremely fast and robust design tool. OCCAM features an extensive set of input parameters, different optimization strategies and output options to provide a high design flexibility for the user. Several methods of collision probability computation are also supported. Its userfriendly graphical interface and intuitive design logic make it really straightforward to master even for nonexperts, and it can be employed either as a standalone tool or in conjunction with other satellite operation planning frameworks. A trial version of this tool called OCCAM lite is available online for the interested potential user at the web page of the Space Dynamics Group: http://sdg.aero.upm.es/index.php/onlineapps/occamlite.=Autor: Claudio Bombardelli //Autor: Juan Luis Gonzalo Gomez//6Autor: Javier Hernando Ayuso The University of Tokyo//7Optimal 3D Orbit Corrections in Curvilinear CoordinatesThe minimumtime, constantthrust orbit correction between two close noncoplanar circular orbits is studied using a relative motion formulation in curvilinear coordinates. The associated optimal control problem in the thrust orientation is tackled using the direct method to numerically solve a diverse set of problems for varying orbital radius and inclination. Additionally, an analytical estimate for the minimumtime inclination change maneuver is obtained. Fundamental changes in the structure of the solution and objective function are highlighted depending on the relation between the required radial displacement, inclination change and available thrust.
 26th AAS/AIAA Space Flight Mechanics Meeting=Autor: Juan Luis Gonzalo Gomez//Autor: Claudio Bombardelli //)Orbit Uncertainty Propagation Using DromoIn this paper a State Transition Matrix for the relative orbital motion expressed in
Dromo variables is obtained using linear theory and applied to propagate the uncertainty
of Near Earth Asteroids under Nbody gravitational perturbation. Dromo is a special
perturbation method that oers important advantages both for the numerical propagation
and for the analytical treatment of perturbed orbital motion. When applied to linear
uncertainty propagation, the proposed method is found to be less complex than nonlinear
methods, both from the mathematical and the computational point of view, and overcomes
fundamental limitations of linear methods based on Cartesian coordinates. A new index is
proposed to assess the strength of nonlinearities across the size of the uncertainty region
during close encounters. When used in combina< tion with the orbit condition code (OCC)
proposed by the Minor Planet Center, the index can be used for predicting the evolution of
the nonlinearities in the uncertainty probability density function and to assess the domain
of applicability of the proposed method. Test cases are conducted using real asteroids
experiencing multiple close encounters.32016 AIAA/AAS Astrodynamics Specialist Conference Long Beach, California9781510831940
13/09/2016
16/09/2016AIAA Space Forum 2016 2Autor: Javier HernandoAyuso University of Tokyo//@Quantification of the Performance of Numerical Orbit PropagatorsThe characterization of the performance of numerical orbit propagation methods is addressed using performance curves. A systematized algorithmic approach is presented to compute the performance curves, identify the linear and nonlinear regimes, and parameterize the linear zone. Also, the performance index concept is introduced, which aims to reduce the meaningful information of a performance curve (ultimately, the performance of the propagation method) into a single figure of merit. Several such performance indices are proposed.17Autor: No Encontrado //Autor: Javier Roa Vicens//Autor: Juan Luis Gonzalo Gomez//Autor: Jesus Pelaez Alvarez//Autor: Claudio Bombardelli //=Spiral Lambert's problem with generalized logarithmic spiralsLambert?s problem subject to a continuous acceleration is solved using the family of generalized logarithmic spirals. Thanks to the existence of two first integrals related to the energy and angular momentum surprising analogies with the Keplerian case are found. A minimumenergy spiral transfer exists. Increasing the value of the constant of the generalized energy yields pairs of conjugate spiral trajectories. The properties of such spirals are strongly connected with the properties of conjugate Keplerian orbits. When the generalized constant of the energy reaches a critical value the two solutions degenerate into a pair of parabolic spirals, one of which connects the two vectors through infinity. From that point the spiral transfers become hyperbolic. Generalized logarithmic spirals admit closedform solutions to all the required magnitudes including the time of flight, providing a deep insight into the dynamics of the problem. In addition, the maximum acceleration along the transfer is found analytically so the solutions that violate the design constraints on the maximum thrust acceleration can be rejected without any further computations. When the time of flight is fixed there is still a degree of freedom in the solution, related to a control parameter. Resonant transfers appear naturally thanks to the symmetry properties of the generalized logarithmic spirals. The problem of designing a lowthrust transfer between two bodies can be reduced to solving the corresponding spiral Lambert?s problem. In order to show the versatility of the method it is applied to the design of an asteroid tour and to explore launch opportunities to Mars..The new SDGcode to solve the Kepler equation 3
The Kepler equation for the elliptical and hyperbolic motion involves a nonlinear function depending on three parameters: the eccentric/hyperbolic anomaly y = E, the eccentricity e and the mean anomaly x = M. For given e and x values the numerical solution of the Kepler equation becomes one of the goals of orbit propagation to provide the position of the object orbiting around a body for some specific time. In this paper, a new approach for solving Kepler equation for elliptical and hyperbolic orbits is developed. The main idea is to provide an initial seed as good as we can to the modified NewtonRaphson method, because when the initial guess is close to the solution, the algorithm is fast, reliable and very stable. This new approach takes advantage of the very good behavior of the Laguerre method and also of the existence of symbolic manipulators which facilitates the obtaining of polynomial approximations. To determine a good initial seed the domain of the equation is discretized in several intervals and for each one of these intervals a fifth degree interpolating polynomial is introduced. The six coefficients of the polynomial are obtained by requiring six conditions at both ends of the corresponding interval. Thus the real function and the polynomial have equal values at both ends of the interval. Similarly relations are imposed for the two first derivatives. Consequently, given e and x = M, selecting the interval according to which M belongs to and using the corresponding polynomial pi(x), we determine the starter value yo = Eo used to start the numerical method. When M is small and e close to unity (singular corner), the Kepler equation has a singular behavior. In this case, an asymptotic expansion in power of the small parameter 1 e (for elliptic case) and e 1 (for hyperbolic case) is obtained to describe the exact solution of the equation.
Two different calculations have been carried out, using standard double precision and quadruple precision. Besides, a complete analysis of the code has been performed to assess the speed of the algorithm and the accuracy. In most of the cases, the seed generated by the Space Dynamics Group at UPM (SDGcode) leads to reach machine error accuracy with the modified NewtonRaphson method with no iterations or just one iteration. Comparing with other methods, the SDGcode provides a greater accuracy when the quadruple precision is applied. The final algorithm is very stable and reliable. The advantage of our approach is its applicability to other problems as for example the Lambert problem for low thrust trajectories.
7Stardust Final Conference on Asteroids and Space DebrisNoordwijk (Netherlands)
03/11/20161Threedimensional generalized logarithmic spiralsThe family of generalized logarithmic spirals including a control parameter is extended to the threedimensional case. The inplane motion is decoupled from the outofplane motion in such a way that the integrals of motion found in the planar problem are still preserved in the threedimensional case. Designing a lowthrust orbit transfer decomposes in two stages: first, orbits are projected on a reference plane and the planar transfer is solved with a generalized logarithmic spiral. Second, the outofplane component of the motion is included in order to target the final orbit. The projection of the threedimensional transfer orbit on the reference plane is a generalized logarithmic spiral. Arbitrary shapebased laws for the 3D motion can be considered. This paper explores a polynomial and a Fourier series shaping method, together with a polynomial steering law. A fictitious lowthrust sample return mission to Ceres is designed to show the versatility of the method.Comentarios Mrito5Seminario "Magnetized Implosions in a MagLIF context"_Seminario: Charla Invitada en el Laboratory for Laser Energetics de la Universidad de Rochester'Seminario "Magnetized Plasma Expansion"gSeminario "Propagator Integral Method For Plasma Physics Kinetic Equations With Practical Applications"fSeminario: Charla invitada en el Deutsche Zentrum fr Luft und Raumfahrt (DLR), Gttingen, Alemania.bVocal del Comit de Direccin de la Divisin de Fsica de Plasmas de la Sociedad Europea de FsicaEl "Board" o Comit de Direccin de la Division de Fsica de Plasmas (PPD) de la Sociedad Europea de Fsica (EPS) tiene las misiones recogidas en los estatutos de la EPS/PPD (http://plasma.ciemat.es/eps/files/2014/01/statutes_EPSPPD.pdf), entre los que se incluye la organizacin de la Conferencia Anual de Fsica de Plasmas de la EPS y la concesin de los prestigiosos premios "Hannes Alfvn" y "Eduard Fabre".ACargo electo, desempeado desde Junio de 2008 hasta Junio de 2016Entidad premiadaEntidad concedenteLugar donde se premiMiembro Sigma Xi Honor SocietyEMiembro permanente de la asociacin de honores en ingeniera Sigma XiSigma Xi Honor Association
Conference ChairmanConference Chairman del 36th International Workshop on High Energy Density Physics with Intense Ion and Laser Beams celebrado en Hirschegg/Austria del 31 <de enero al 5 de febrero de 2016
31/01/2016Hirschegg/AustriaCResponsabilidades en congresos y reuniones tcnicas internacionales3Miembro de la comisin evaluadora de DOCENTIA (UPM)UPMOtro tipo de responsabilidadiRevisor en la dcimo cuarta Conferencia Iberoamericana en
Sistemas, Ciberntica e Informtica: CISCI 2015
08/07/2016Orlando (Florida)7Subdirector de Extensin Universitaria y Alumnos ETSIAE<Subdirectora de Extensin Universitaria y Alumnos  ETSIAE
14/12/2013ETSI Aeronutica y del Espacio/Responsabilidades en cargos de gestin en I+D+iNombre Apellidos categoraentidadTutorPABLOSOLANO LPEZBECARIO OTTJose Manuel Donoso VargasJORGEGONZALEZ MUOZDAVIDEAMATO 'CONTRATADO CON CARGO A PROYECTO UPMOTTClaudio Bombardelli Sandra PilarTierno Gomez(PIF  PERSONAL INVESTIGADOR EN FORMACIONLuis Conde LopezPasqualeDinoi .Jesus Maria Gomez GoiJAVIERCALDERON SANCHEZCONTRATADOS PREDOCTORALESDaniel Duque CampayoVIRGINIA
RAPOSO PULIDOJesus Pelaez AlvarezJULIUSDAMBA
JUAN LUIS
GONZALO GOMEZ
ROA VICENSCLAUDIOBOMBARDELLI "DOCTOR CONTRATADO PROGRAMA OFICIAL] _ X
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