Global ETD Search

1	A stability result for the lunar three body problem Bowles, Mark Nicholas January 2000 (has links) No description available. 519 Hamiltonian; Sun; Earth; Moon
2	Comparison of the shock arrival times for Earth-directed ICMEs provided by the WSA-Enlil+Cone model and in-situ observations at L1: A Case Study Werner, Anita Linnéa Elisabeth January 2016 (has links) A case study which examines the agreement between prediction and data is performed for three, complex interplanetary shocks which were detected at the Sun-Earth Lagrange point L1 and induced moderate to intense geomagnetic storms. We use model output from previous runs of the coupled coronal-heliosphere WSA-Enlil+Cone model, available through the Community Coordinated Modeling Center (CCMC), and in-situ data from the OMNI data set. Code written in MATLAB is used to compare the model output with the in-situ measurements of the interplanetary magnetic field as well as the density, speed and temperature of the solar wind. In addition, the difference between the predicted and actual shock arrival time is computed and regions of potential temperature depression are identified. A considerable discrepancy is found between data and model for the studied events. The main reason is deemed to be an inadequate representation of the ambient solar wind as well as the complex interactions between interplanetary coronal mass ejections and corotating interaction regions. We suggest future steps to be taken for the further development of the model as well as for the general understanding of space weather and the Sun-Earth connection. / Denna fallstudie undersöker överensstämmelsen mellan modell och data för tre interplanetära chockvågor, som kunde detekteras vid jordens Lagrangepunkt 1, och som orsakade geomagnetiska stormar av måttlig till kraftig styrka. Vi använder oss av tidigare genomförda körningar av den sammansatta WSA-Enlil+Cone modellen, som avbildar fortplantningen av temporära störningar med ursprung i solens korona, såsom koronamassutkastningar, ut i heliosfären. Modellen gjordes tillgänglig av Community Coordinated Modeling Center (CCMC) och datan inhämtades från OMNI. Kod skriven i MATLAB nyttjades för att göra en jämförelse mellan modell och faktiska mätningar av det interplanetära magnetfältet samt solvindens hastighet, densitet och temperatur. Utöver detta, beräknas också skillnaden mellan förväntad och faktisk ankomsttid av respektive interplanetär chock, och tidsperioder med en temperatursänkning utöver det normala identifieras. Vi finner en omfattande avvikelse mellan modell och data, i synnerhet för de fall där på varandra följande koronamassutkastningar förväntas interagera eller rent av slås ihop samt för uppskattningen av den omgivande solvindens egenskaper och det interplanetära fältet under pågående geomagnetisk störning. Interaktionen mellan koronamassutkastningar och närliggande ko-roterande interaktionsregioner har ej heller återskapats väl av modellen ifråga. Slutligen ger vi förslag på möjliga, framtida åtgärder som kan bör tas i åtanke vid konstruerandet av framtida versioner av nämnda modell, liksom för den allmänna förståelsen för rymdvädrets inverkan på Jorden. CME ICME CIR WSA-Enlil+Cone CCMC ACE SAT St. Patrick Sun-Earth connection
3	Hybrid Station-Keeping Controller Design Leveraging Floquet Mode and Reinforcement Learning Approaches Andrew Blaine Molnar (9746054) 15 December 2020 (has links) The general station-keeping problem is a focal topic when considering any spacecraft mission application. Recent missions are increasingly requiring complex trajectories to satisfy mission requirements, necessitating the need for accurate station-keeping controllers. An ideal controller reliably corrects for spacecraft state error, minimizes the required propellant, and is computationally efficient. To that end, this investigation assesses the effectiveness of several controller formulations in the circular restricted three-body model. Particularly, a spacecraft is positioned in a L<sub>1</sub> southern halo orbit within the Sun-Earth Moon Barycenter system. To prevent the spacecraft from departing the vicinity of this reference halo orbit, the Floquet mode station-keeping approach is introduced and evaluated. While this control strategy generally succeeds in the station-keeping objective, a breakdown in performance is observed proportional to increases in state error. Therefore, a new hybrid controller is developed which leverages Floquet mode and reinforcement learning. The hybrid controller is observed to efficiently determine corrective maneuvers that consistently recover the reference orbit for all evaluated scenarios. A comparative analysis of the performance metrics of both control strategies is conducted, highlighting differences in the rates of success and the expected propellant costs. The performance comparison demonstrates a relative improvement in the ability of the hybrid controller to meet the mission objectives, and suggests the applicability of reinforcement learning to the station-keeping problem. Aerospace Engineering station-keeping floquet mode reinforcement learning circular restricted three-body problem sun-earth
4	Trajectory Design Strategies from Geosynchronous Transfer Orbits to Lagrange Point Orbits in the Sun-Earth System Juan Andre Ojeda Romero (11560177) 22 November 2021 (has links) <div>Over the past twenty years, ridesharing opportunities for smallsats, i.e., secondary payloads, has increased with the introduction of Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) rings. However, the orbits available for these secondary payloads is limited to Low Earth Orbits (LEO) or Geostationary Orbits (GEO). By incorporating a propulsion system, propulsive ESPA rings offer the capability to transport a secondary payload, or a collection of payloads, to regions beyond GEO. In this investigation, the ridesharing scenario includes a secondary payload in a dropped-off Geosynchronous Transfer Orbit (GTO) and the region of interest is the vicinity near the Sun-Earth Lagrange points. However, mission design for secondary payloads faces certain challenges. A significant mission constraint for a secondary payload is the drop-off orbit orientation, as it is dependent on the primary mission. To address this mission constraint, strategies leveraging dynamical structures within the Circular Restricted Three-Body Problem (CRTBP) are implemented to construct efficient and flexible transfers from GTO to orbits near Sun-Earth Lagrange points. First, single-maneuver ballistic transfers are constructed from a range of GTO departure orientations. The ballistic transfer utilize trajectories within the stable manifold structure associated with periodic and quasi-periodic orbits near the Sun-Earth L1 and L2 points. Numerical differential corrections and continuation methods are leveraged to create families of ballistic transfers. A collection of direct ballistic transfers are generated that correspond to a region of GTO departure locations. Additional communications constraints, based on the Solar Exclusion Zone and the Earth’s penumbra shadow region, are included in the catalog of ballistic transfers. An integral-type path condition is derived and included throughout the differential corrections process to maintain transfers outside the required communications restrictions. The ballistic transfers computed in the CRTBP are easily transitioned to the higher-fidelity ephemeris model and validated, i.e., their geometries persist in the ephemeris model. To construct transfers to specific orbits near Sun-Earth L1 or L2, families of two-maneuver transfers are generated over a range of GTO departure locations. The two-maneuver transfers consist of a maneuver at the GTO departure location and a Deep Space Maneuver (DSM) along the trajectory. Families of two-maneuver transfers are created via a multiple- shooting differential corrections method and a continuation process. The generated families of transfers aid in the rapid generation of initial guesses for optimized transfer solutions over a range of GTO departure locations. Optimized multiple-maneuver transfers into halo and Lissajous orbits near Sun-Earth L1 and L2 are included in this analysis in both the CRTBP model and the higher-fidelity ephemeris model. Furthermore, the two-maneuver transfer strategy employed in this analysis are easily extended to other Three-Body systems. </div> Aerospace Engineering Dynamical Systems Theory crtbp GEOSYNCHRONOUS ORBIT periodic orbits quasi-periodic Sun-Earth system Lagrange point
5	Barns tankar och idéer om himlakropparnas rörelse : Vanliga astronomiska missförstånd / Children’s Thoughts and Ideas About Celestial Motion : Common astronomical misconceptions Johansson, Elin January 2014 (has links) Sammanfattning De flesta barn fängslas och visar intresse för temat rymden och finner vanligtvis att det är ett mycket intressant ämne. Fokusgruppen har varit elever i årskurs 4-6 och efter några större bortfall var det slutligen elever ifrån 8 klasser som deltog, totalt 94 elever. Eleverna fick svara på en enkät där eleverna i både text och bild bland annat fick förklara hur de trodde att objekten i sol–jord–månsystemet samverkade och rörde sig i förhållande till varandra, vad de placerade i centrum för detta system, hur de såg på orsaken till årstider samt varför vi har dag och natt. De två pedagogerna som undervisade klasserna fick svara på några frågor om hur de såg på undervisningen om astronomi, om den undervisningsmetod de använde sig av och på elevernas lärande och förståelse för ämnet astronomi. I denna undersökning kunde samma typer av missuppfattningar ses hos dessa elever, som de missuppfattningar som har dykt upp i en rad olika undersökningar som genomförts tidigare år med andra barn ifrån olika länder. Några av de missuppfattningar som fanns hos eleverna i denna undersökning var bland annat att jorden var mittpunkten, något som en femtedel av eleverna visade. Att sol och måne låg i samma omloppsbana runt jorden, årstiderna orsakas av att avståndet till solen förändras och att dag/natt beror på jordens omloppsbana runt solen var några andra missuppfattningar som rådde bland eleverna. Användandet av konkret material och 3D-modeller i undervisningen om rymden tycks vara en viktig del för elevernas förståelse av området. Nyckelord: undervisning om rymden – astronomiska missförstånd – årstider – dag/natt – omloppsbanor i sol–jord–månsystemet / Abstract Most children find astronomy an interesting subject and usually show an interest during lessons about the subject. The focus group in this paper is Swedish students in school year 4-6. In total there were 94 students from eight classes who answered the survey with simple drawings and explanations about for example how they thought the objects Sun–Earth–Moon orbit each other, which object they placed as the center in this system, what causes season and the reason behind day and night. Two teachers whom educate the students answered some questions about their teaching method, their thoughts about the subject in question and the students learning and understanding of astronomy. In the study that are presented in this paper the same types of astronomical misconceptions can be seen amongst these students, that has been shown in similar studies of children all over the world. 20 % of the children in this study showed an earth centered Sun–Earth–Moon system. Other misconceptions that were shown was: the sun and the moon shares the same orbit around the earth, that the seasons are caused by the distance to the sun changing and that day and night happens because the earth orbits the sun. The use of concrete material and 3D-models in the education seemed to be important for the students understanding of the subject. Keywords: Astronomy education – astronomy misconceptions – seasons – day/night – Celestial Motion in the Sun–Earth–Moon system Astronomy education astronomy misconceptions seasons day/night undervisning om rymden astronomiska missförstånd årstider dag/natt omloppsbanor i sol–jord–månsystemet
6	Novel Approaches to the Design of Domestic Solar Hot Water Systems Guarnieri, Raniero Alberto January 2005 (has links) Domestic solar hot water units, if properly designed, are capable of providing all hot water needs in an environmentally friendly and cost-effective way. Despite 50 years of development, commercial technology has not yet achieved substantial market penetration compared to mainstream electric and gas options. Therefore, alternate designs are warranted if they can offer similar or greater performance for a comparable cost to conventional units. This study proved that such alternatives are possible by designing and testing two novel solar hot water systems (SHWS). The first system used compound parabolic collector (CPC) panels to concentrate solar energy and produce steam. The steam moved from a rooftop downward into a heat exchange pipe within a ground level water tank, heating the water, condensing and falling into a receptacle. The operation was entirely passive, since the condensate was pulled up due to the partial vacuum that occurred after system cooling. Efficiencies of up to 40% were obtained. The second system used an air heater panel. Air was circulated in open and closed loop configuration (air recycling) by means of a fan/blower motor and was forced across a compact heat exchanger coupled to a water tank. This produced a natural thermosiphon flow heating the water. Air recycling mode provided higher system efficiencies: 34% vs. 27%. The concurrent development of an analytical model that reasonably predicted heat transfer dynamics of these systems allowed 1) performance optimisation for specific input/starting operating conditions and 2) virtual design improvements. The merit of this model lay in its acceptable accuracy in spite of its simplicity. By optimising for operating conditions and parameter design, both systems are capable of providing over 30 MJ of useful domestic hot water on clear days, which equates roughly to an increase of 35°C in a 200 L water tank. This will satisfy, on average, daily hot water requirements for a 4-person household, particularly in low-latitude regions (eg. Queensland). Preliminary costing for these systems puts them on par with conventional units, with the passive, remotely coupled, low maintenance, CPC SHWS comparable to higher end models. The air heater SHWS, by contrast, was much more economical and easier to build and handle, but at the trade-off cost of 1) the need for an active system, 2) increased maintenance and running costs and 3) the requirement for a temperature control mechanism that would protect the panel body by dumping hot air trapped inside if stagnation were to occur. Domestic Solar Hot Water Systems Concentrating Optics Compound Parabolic Collectors Solar Selective Surface Self-Pump Air Heater Panel Compact Heat Exchanger Sun-Earth Geometry
7	Étude de la dynamique autour et entre les points de Lagrange de modèles Terre-Lune-Soleil cohérents / Study of dynamics about and between libration points of Sun-Earth-Moon coherent models Le Bihan, Bastien 19 December 2017 (has links) Au cours des dernières décennies, l’étude de la dynamique autour des points de Lagrange des systèmes Terre-Lune (EMLi) et Terre-Soleil (SELi) a ouvert de nouvelles possibilités pour les orbites et les transferts spatiaux. Souvent modélisés comme des Problèmes à Trois Corps (CR3BP) distincts, ces deux systèmes ont également été combinés pour produire des trajectoiresà faible coût dans le système Terre-Lune-Soleil étendu. Cette approximation (PACR3BP) a permis de mettre en évidence un réseau à faible énergie de trajectoires (LEN) qui relie la Terre, la Lune, EML1,2 et SEL1,2. Cependant, pour chaque trajectoire calculée, le PACR3BP nécessite une connexion arbitraire entre les CR3BPs, ce qui complique son utilisation systématique. Cette thèse vise à mettre en place une modélisation à quatre corps non autonome pour l’étude du LEN basé sur un système Hamiltonien périodique cohérent, le Problème Quasi-Bicirculaire (QBCP). Tout d’abord, la Méthode de Paramétrisation est appliquée afin d’obtenir une représentation semi-analytique des variétés invariantes autour de chaque point de Lagrange. Une recherche systématique de connexions EML1,2-SEL1,2 peut alors être effectuée dans l’espace des paramètres : les conditions initiales sur la variété centrale-instable de EML1,2 sont propagées et les trajectoires résultantes sont projetées sur la variété centrale de SEL1,2 . Un transfert est détecté lorsque la distance de projection est proche de zéro. Les familles de transfert obtenues sont corrigées dans un modèle newtonien haute-fidélité du système solaire. La structure globale des connections est largement préservée et valide l’utilisation du QBCP comme modèle de base du LEN. / In recent decades, the dynamics about the libration points of the Sun-Earth (SELi) and Earth-Moon (EMLi ) systems have been increasingly studied and used, both in terms of transfer trajectory computation and nominal orbit design. Often seen as two distinct Circular Restricted Three Body Problems (CR3BP), both systems have also been combined to produce efficient transfers in the Sun-Earth-Moon system. This patched CR3BP approximation (PACR3BP) allowed to uncover a low-energy network (LEN) of trajectories that interconnect the Earth, the Moon, EML1,2 and SEL1,2 . However, for every computed trajectory, the PACR3BP requires an arbitrary connection between the CR3BPs, which limits its use in a systematic tool. This thesis introduces a single non-autonomous four-body framework for the study of the LEN based on a coherent periodically-forced Hamiltonian system, the Quasi-Bicircular Problem (QBCP). First, the Parameterization Method is applied in order to obtain high-order, periodic, semi-analytical parameterizations of the invariant manifolds about each libration point. A systematic search for EML1,2 -SEL1,2 connections can then be performed in the parameterization space: initial conditions on the center-unstable manifold at EML1,2 are propagated and projected on the center manifold at SEL1,2. A transfer is found each time that the distance of projection is close to zero. These trajectories are refined as solutions of a Boundary Value Problem, which uncover families of natural transfers, later transitioned into a higher-fidelity model. The global structure of the connecting orbits is largely preserved, which validates the QBCP as a relevant model for the LEN. Système Terre-Lune-Soleil Problème à quatre corps restreint Point de Lagrange Variétés invariantes Transferts libres Sun-Earth-Moon system Restricted four-Body problem Libration point Invariant manifolds Natural transfers 510
8	Spektrální vlastnosti denního světla jako časoprostorová funkce / Spectral properties of daylight as time-spatial function Mayer, Jan January 2009 (has links) Graduation thesis describes basic data about Sun, suns constant, solar radiation thoroughfare by the earth's atmosphere. Thesis describes effects of components of optical radiation and physical character of solar radiation. Thesis also describes character of day lighting in nature, spectral distribution of natural lighting, average time of sunshine. The next point of thesis is description of measuring equipment Konica Minolta. In chapter measuring procedure is described measuring process of the sky radiance. Measurement analysis is mentioned in conclusion.
9	Characterization of Quasi-Periodic Orbits for Applications in the Sun-Earth and Earth-Moon Systems Brian P. McCarthy (5930747) 17 January 2019 (has links) <div>As destinations of missions in both human and robotic spaceﬂight become more exotic, a foundational understanding the dynamical structures in the gravitational environments enable more informed mission trajectory designs. One particular type of structure, quasi-periodic orbits, are examined in this investigation. Speciﬁcally, eﬃcient computation of quasi-periodic orbits and leveraging quasi-periodic orbits as trajectory design alternatives in the Earth-Moon and Sun-Earth systems. First, periodic orbits and their associated center manifold are discussed to provide the background for the existence of quasi-periodic motion on n-dimensional invariant tori, where n corresponds to the number of fundamental frequencies that deﬁne the motion. Single and multiple shooting diﬀerential corrections strategies are summarized to compute families 2-dimensional tori in the Circular Restricted Three-Body Problem (CR3BP) using a stroboscopic mapping technique, originally developed by Howell and Olikara. Three types of quasi-periodic orbit families are presented: constant energy, constant frequency ratio, and constant mapping time families. Stability of quasi-periodic orbits is summarized and characterized with a single stability index quantity. For unstable quasi-periodic orbits, hyperbolic manifolds are computed from the diﬀerential of a discretized invariant curve. The use of quasi-periodic orbits is also demonstrated for destination orbits and transfer trajectories. Quasi-DROs are examined in the CR3BP and the Sun-Earth-Moon ephemeris model to achieve constant line of sight with Earth and avoid lunar eclipsing by exploiting orbital resonance. Arcs from quasi-periodic orbits are leveraged to provide an initial guess for transfer trajectory design between a planar Lyapunov orbit and an unstable halo orbit in the Earth-Moon system. Additionally, quasi-periodic trajectory arcs are exploited for transfer trajectory initial guesses between nearly stable periodic orbits in the Earth-Moon system. Lastly, stable hyperbolic manifolds from a Sun-Earth L<sub>1</sub> quasi-vertical orbit are employed to design maneuver-free transfer from the LEO vicinity to a quasi-vertical orbit.</div> Aerospace Engineering aerospace engineering trajectory trajectory design astrodynamics three body three body mechanics circular restricted three body problem CR3BP quasi-periodic orbits periodic orbits orbit mechanics celestial mechanics dynamical systems dynamical systems theory dynamics applications orbits astronautics differential corrections invariance invariant circle invariant torus torus invariant tori stroboscopic mapping manifolds Sun-Earth system Earth-Moon system stability multiple shooting stroboscopic map eclipse avoidance vertical orbit halo orbit distant retrograde orbit quasi-halo quasi-vertical lissajous quasi-DRO DRO NRHO quasi-NRHO synodic resonance trajectory arcs mission design astromechanics spaceflight mechanics dynamical structures

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