1,721,041 research outputs found
Satellite Maneuver Detection and Estimation with Radar Survey Observations
Full text linkThe space environment is rapidly getting congested, inducing a growth of the risk of collision between Resident Space Objects (RSOs). The validity of collision risk assessment depends on the quality of the catalogs of RSOs, which shall be as accurate and up-to-date as possible. Maneuvers of operational satellites represent a problem, because, if not correctly detected and estimated, they could lead to catalog degradation or pollution. In this paper, a novel approach to tackle the maneuver detection and estimation problem is presented. The methodology, which is part of the association problem between tracks and objects, is intended to be included in real-time cataloging systems to increase their flexibility. This paper is a continuation, extension and improvement of a former work, where maneuver estimation was carried out with optical observations. The estimation algorithm is extended to radar observations with the inclusion of a new dynamical model. The joint detection and estimation scheme is tested in a simulated maintenance chain with tracks and orbits from a single satellite. In this scenario, the output of the maneuver estimation is then used as an a-priori guess in high-fidelity orbit determination, which is refined and used to compute a post-maneuver orbit. The results of the application of the detection and estimation algorithm within the simulated chain are presented, highlighting the advantages and validating the methodology, providing a basis for a wider multi-target multi-sensor association framework, with the final goal of solving the association problem with data from survey activities
CubeSat Landing Simulations on Small Bodies using Blender
Full text linkLanding on small-bodies is a very challenging problem that requires high degrees of robustness and autonomy. Being able to perform simulations with great flexibility and accuracy is paramount for the development and design of landing systems. To this end, contact dynamics plays a fundamental role and is often handled by complex tools that require large amount of development and validation efforts and very specific expertise. In the last decade, the Visual Effects (VFX) industry has developed numerous suites that deal with contact dynamics frameworks. In this work, the possibility of leveraging on the work of the VFX industry by using Blender, one of these tools, as the source for the contact dynamics modelling is investigated. This research focuses on the description of the methodology used for the landing simulations and the validation of the tool developed. A step-by-step guide through the simulation setup is given, discussing how the wrapping GNC simulator and Blender interact. Validation tests for the different parameters and dynamic models involved in the simulations are also presented. The results refer to the landing of a CubeSat in the crater region of an asteroid. In particular, the artificial crater that will be generated on Dimorphos by NASA's DART impact in late September 2022, is considered in the simulations presented in this work. Safety maps are generated by post-processing these results, and are used to assess different landing strategies or site-selection criteria on the Dimorphos crater study case. Finally, the role of the developed tool in optimising the use of space resources and its contribution to landing design strategies is discussed
Optimal Ascent Trajectory of a Small Launcher
Full text linkThis work consists mainly on the optimization of an ascent trajectory to a given orbit
and a comparison between launching to the orbit from ground and from a carrying air
vehicle (vertical and horizontal launch, respectively). Moreover, a series of sensitivity
analysis were also done in order to highlight the importance of the atmospheric models,
the constraints imposed and the dependence on the initial guess of these kind of numerical
procedures. A small survey was also performed to select the formulation, direct or
indirect, that was better to perform the analysis. The reason why this topic was chosen is
because of the interest of the author not only in space and mathematical problems, but also
in the development of numerical solvers and coding. With this document, both interests
can be joined together by the development of an optimization of trajectories code.
The study was done mainly in three blocks: the first block consists on the validation of
the mathematical and dynamical model for both indirect and direct optimization formulations.
For this case, the first stage of the ascension profile of the Apollo 8 mission was
selected. Together with the validation, a sensitivity analysis with different initial guesses
was carried out. In this block it is shown how even small variations in the initial guess
can lead to highly different results. It is in this part where the decision between direct and
indirect formulation is taken. The second block consists on the different analyses done to
study the influence of the model and the linear and non-linear constraints in these highly
non-linear problems. Moreover, the atmospheric model, in particular the one regarding
the density, shown up to be also determinant in the output of the solutions. Finally, the
third part consists on the optimization of an ascent trajectory and a later comparison with
an air launch. Then, a simple cost model will be presented so that it can be demonstrated
from an industrial point of view that there are some situations in which horizontal launch
is more suitable from the economic point of view than vertical launch.
The two first blocks were carried out by a code entire developed by the author. The
optimization procedure of the third block was done with an already developed code in
order to obtain results of a higher reliability. Finally, the cost model that was adopted was
the one obtained from a later given source.
At the end of this work the author has understood the difficulties related to numerical
methods, more specifically those regarding optimization of trajectories. Among these
difficulties one could find the selection of the atmospheric model, selection of the initial
guess or deciding whether to use a direct or an indirect formulation. Besides, the author
has also been able to acquire a deeper knowledge about a topic in which it has been always
interested.Ingeniería Aeroespacia
Impulsive and low-thrust optimal trajectories for asteroid mining
Full text linkNear – Earth Asteroids (NEA’s) are celestial bodies which have ended up falling into orbits in
the vicinity of the Earth due to the gravitational interactions these bodies have undergone
in the past. As a result, they have posed a new threat to human existence since the risk of
collision between the Earth and one of these bodies is certainly possible. Nevertheless, NEA’s
have also presented humanity with the opportunity of redefining its frontiers and changing
the way in which the economical and development systemcan be conceived, since studies
have suggested that these bodies are rich in natural resources such as water and precious
metals.
As a result, NEA’s have become attractive targets for miningmissions. For this operations
to be carried out the first step is performing a preliminary study of the trajectories that
could take a mission to the asteroid’s surface and return it back to Earth once the desired
materials have been extracted. To that end, this thesis addresses the determination of
optimal trajectories towards ten asteroids selected for the purpose, which include: Ryugu,
1989ML, Nereus, Didymos, 2011 UW158, Anteros, 2001 CC21, 1992 TC, 2001 SG10 and 2002
DO3.
Results have been obtained for both, chemical propulsion systems and ion engines.
Initially, a first study was carried out to determine the pork-chop plots characterizing each of
the transfers and the mission with minimum ¢V (including outbound and inbound flights)
was analyzed. Then, with the objective of optimizing the whole mission, the Non-dominated
Sorting Genetic AlgorithmII (NSGA-II) was used so as to broaden the trajectory possibilities
and performa study which also accounted for economical and time factors.With the use of
NSGA-II, multi-revolution transfers as well as gravity assist maneuvers around Venus and
Mars have been studied. In addition, multi-revolution trajectories using low-thrust were
also considered.
The results presented in this thesis show the launching opportunities as well as the
optimized asteroid mining missions for both type of propulsion methods being considered.
In addition, a full development and analysis of the obtained values is carried out for asteroids
Ryugu and Didymos.Ingeniería Aeroespacial (Plan 2010
High-Fidelity Simulator of High-Altitude Platforms
Full text linkThis document will be focused on the development of a comprehensive study around
high-altitude platforms and the validation of a high-fidelity numerical simulator for them,
more specifically for weather balloons. These high-altitude balloons are essential for near
space experiments, as any other mean will be either impossible or much more expensive
to perform that kind of tasks.
This project will upgrade an existing simulator in order to properly estimate the burst
point of the balloon during its flight, as well as to add the calculation of the landing
point of the platform equipped with a parachute. This simulator will take into account
several variables that take an important role in the evolution of the balloon trajectory
like temperatures and pressures, together with the evolution of the radius of the balloon.
Moreover, the program will use high fidelity predictions of the winds and temperatures
of the environment where the simulated mission takes place, provided by the National
Oceanic and Atmospheric Administration (NOAA).
Besides the simulator improvement, a platform prototype for an experimental launch
will be set up, securing the functionality of its tracking and communication systems to
properly send data about its position to the control station, and the recording of all the
information extracted from the mission. Moreover, the decoding procedure followed to
extract the location information from the message sent by the platform will be explained.
As this experimental launch is scheduled for the near future, the results from the simulator
will be compared with the data retrieved in an early mission of a high-altitude
balloon in order to check its validity and efficiency. Moreover, to complete the analyses
performed, a comparison between this simulator results and the ones extracted from an
external online predictor, is done together with an uncertainty analysis around weather
information and ascent parameters.Ingeniería Aeroespacia
Trajectory optimization for asteroid mining
Full text linkNear Earth Asteroids might become key in the future development of mining and space industry.
Their exploitation would give access to a huge amount of minerals and metals that could be used
to create an "in-space manufacturing industry" and that could be used also to support deep
space missions and stations through in situ resource utilization. However, a deep knowledge of
minearologic composition and dynamic distribution of these bodies would be required in order
to attain these achievements.
This work tries to shed light to the matters of what NEAs should be considered in a mining
project, what orbital parameters are going to in
uenced energetic cost required to reach them
and how transfer trajectories could be optimized. A total of twelves NEAs have been analysed
through four di erent methods, employing an straightforward resolution of Lambert's Problem
and genetic algorithms. Optimization of the previous trajectories have been studied through a
Patched Conics Method, solving it also making use of a direct approach and with NSGA-II.Ingeniería Aeroespacia
A stochastic orbital propagation scheme applied to re-entry analysis
Full text linkLAUREA MAGISTRALENegli ultimi anni si è registrato un forte aumento del traffico spaziale. Questo fatto ha generato la necessità di produrre regolamentazioni per l'uso sostenibile dello spazio, oltre a fornire servizi agli operatori satellitari e agli altri attori coinvolti. Tra questi servizi vi è l'analisi del rientro, sia per verificare il rispetto delle normative sia per produrre avvisi per i gestori del traffico aereo o i servizi di protezione civile. L'obiettivo principale dell'analisi del rientro di un veicolo spaziale nell'atmosfera è determinare il momento e la posizione del decadimento, cruciale per valutare i rischi di impatto al suolo. Questo rappresenta una sfida complessa a causa della natura stocastica dell'evoluzione della traiettoria negli strati più densi dell'atmosfera. Anche variazioni minime nel tempo possono portare a differenze significative nel punto di impatto del veicolo spaziale. Inoltre, la frammentazione del s/c è altamente probabile, complicando ulteriormente le previsioni.
Una delle sfide nell'analisi del rientro è la corretta gestione dell'incertezza. L'incertezza può derivare da effetti non modellati, ad esempio, il modo in cui la dinamica di assetto non controllata o la conoscenza insufficiente delle forze coinvolte influenzano l'evoluzione del rientro. In questo studio si propone l'esplorazione di diversi metodi per affrontare le sfide precedenti nella fase iniziale di un rientro. L'obiettivo è implementare un propagatore stocastico per quantificare adeguatamente l'incertezza nella propagazione dello stato di un veicolo spaziale in rientro e confrontarlo con uno schema di propagazione deterministico ad alta fedeltà. Da un punto di vista dinamico, si confronteranno quindi due modelli: un semplice modello di massa puntiforme con una rappresentazione relativamente basica delle forze perturbanti, che prevede uno schema di propagazione stocastico, e un modello a sei gradi di libertà, che include la dinamica di assetto e prevede una propagazione deterministica. Il simulatore 6DOF potrebbe includere la possibilità di un controllo attivo e sarà validato rispetto ai dati ottenuti durante i rientri di GOCE e Roseycubesat-1. Per quanto riguarda l'integrazione, vengono impiegati due schemi separati: per il caso deterministico si seleziona un metodo di Runge-Kutta di ordine 4, mentre per il secondo caso si propone un Runge-Kutta stocastico di ordine 4, originariamente concepito per affrontare equazioni differenziali stocastiche. Ciò è possibile se modelliamo la dinamica del veicolo spaziale come un sistema stocastico. Le prestazioni dei due algoritmi saranno confrontate, in particolare sulla capacità di quello stocastico di fornire una previsione raffinata con un modello dinamico meno accurato. L'approccio proposto sarà testato in scenari rappresentativi per avere una chiara visione sull'affidabilità di un propagatore stocastico. Un metodo MC sarà utilizzato per ottenere statisticamente la finestra di rientro.Recent years have seen a large increase in space traffic. This fact has generated the need to produce regulations for the sustainable use of space, as well as provide services to satellite operators and other involved actors. Among these services is re-entry analysis, both to verify that the regulations are complied with and to produce notices to air traffic managers or civil protection services. The primary goal of analysing a spacecraft's re-entry into the atmosphere is to determine the time and location of decay, which is crucial for assessing ground impact risks. This is a complex challenge due to the stochastic nature of trajectory evolution in the denser layers of the atmosphere. Even minor time variations can lead to significant differences in the spacecraft's touchdown location. Additionally, fragmentation of the s/c is highly probable, further complicating predictions.
One of the challenges when analysing re-entry is the correct management of the uncertainty. Uncertainty can come from non-modelled effects, for example, how uncontrolled attitude dynamics, or insufficient knowledge of the forces involved affect the re-entry evolution. In this study, the exploration of different methods to address the previous challenges in the initial stage of a re-entry is proposed. The goal is to implement a stochastic propagator to adequately quantify the uncertainty in the state propagation of a re-entering spacecraft, and compare it with a high-fidelity deterministic propagation scheme. Therefore, from a dynamical point of view, two models are to be compared: a simple point mass model with relatively basic representation of the perturbing forces, involving a stochastic propagation scheme, and a full 6DOF model, including attitude dynamics and involving deterministic propagation. The 6DOF simulator could include the possibility of having active control and will be validated against the data obtained during GOCE and Roseycubesat-1 re-entry. Regarding the integration, two separate schemes are employed: for the deterministic case a RK4 method is selected, while for the second case a SRK4 is proposed, originally designed to tackle stochastic differential equations. This is possible if we model the spacecraft’s dynamics as a stochastic system. The performance of the two algorithms will be compared, especially on the capability of the stochastic one to have a refined prediction with a less accurate dynamical model. The proposed approach will be tested in representative scenarios to have a clear vision on the reliability of a stochastic propagator. A MC method will be used for statistically obtaining the re-entry window
Logistics analysis of a in-situ resource utilisation mission to the Moon
Full text linkSpace exploration has reached a development stage whose main objective is to closely investigate
and analyze celestial bodies. Due to its proximity to the Earth, the Moon is an evident starting
point for this analysis.
The Moon presents an entirely di erent environment from that found on Earth, and is extremely
hostile to human beings. The absence of an atmosphere causes critical conditions, such as absence
of oxygen, vacuum, widely-varying temperatures and severe solar radiation.
However, the lunar surface presents an opportunity to solve some of these issues. The lunar regolith
(moon-dust) contains hydrogen, ice-water and other elements that may be employed by alternative
methods to create a habitable environment.
In this context, the scope of this research is to analyze the feasibility of ful lling a long-term mission
on the Moon using exclusively local resources, with no dependency on the Earth. This study
considers only currently-available ISRU technology, with the purpose of verifying if improvements
to existing technology are required to complete a mission of these characteristics.Ingeniería Aeroespacia
Preliminary design of an attitude control system for a high altitude platform
Full text linkWithin this document the process of developing different designs for the hardware of an attitude control system
based on reaction wheels implemented in a high altitude platform is depicted along with a review of the most
common attitude control systems used currently by different members of the aerospace industry.
The process consists mainly in three parts: First, developing a simulation environment that recreates the
conditions in which the platform is expected to operate and implement the physical laws that govern the motion
of these kind of artifacts, and is able to compute the geometrical characteristics of the different reaction wheels
tested. Secondly the performance of different candidate designs of reaction wheels is tested and analyzed. And
finally a selection between all these candidates is performed taking into account different elements like the time
that each design takes to correct the attitude of the platform, the weight of the wheels, the required angular
velocity to maintain the desired attitude and the cost of the material employed.Ingeniería Aeroespacia
Maneuvering Target Tracking Methods for Space Surveillance
No full textEarth orbits are a valuable natural resource that shall be preserved. A myriad of services currently relies on orbital stations, most of which support modern human society. To name a few, global navigation satellite services and weather forecasting, crucial for the vast majority of the population, require sensors and stations in Earth orbit. Recently, the space industry has seen a considerable decrease in launch and development costs, so access to space is more affordable than ever before. The latter has opened the gate for new actors in the space domain, such as startups and universities, which now operate small-sized spacecraft (up to 500 kg) at low orbital altitudes. This breed of new satellites adds up to an already numerous background population, composed not only of operative satellites but also derelict rockets and spacecraft as well as fragments originated from break-up events or explosions and in-orbit collisions. It is this last subset of the Earth
orbital population that alarms the space community: for a sufficiently high congestion level, a single collision can trigger a cascade of additional events to the point that every object placed in orbit is guaranteed to collide against a neighboring fragment in a relatively short period of time. To prevent this catastrophic situation, the Earth orbital space is continuously monitored by surveillance networks composed of ground and space-based sensors of different types. Data acquired by these sensors is processed and fused with information coming from satellite operators to elaborate and maintain a comprehensive list, or catalog, of objects in Earth orbit. Generating a labelled map of objects can help to prevent future in-orbit collisions: by running one-to-one conjunction analysis over the entire population, it is possible to identify potentially hazardous conjunctions and issue warnings to spacecraft operators so they can take remedial action. Accurately tracking space objects with surveillance sensors is a complex task, especially if it is to be done automatically. In particular, the integrity of space object catalogs is compromised when spacecraft perform maneuvers and their operators do not report them in a timely manner, mainly because automated space surveillance and tracking systems rely on natural satellite motion or very simple maneuver models at best. This thesis is aimed at advancing the tools and techniques required for automated space surveillance and tracking in the presence of unknown maneuvers, emphasizing on the definition of suitable maneuver models for space objects. One of the main problems associated with orbital maneuvers is data association, this is, being able to assess whether certain observation corresponds to a
given target following a maneuver. In general, it is not easy to provide evidence supporting measurement to object correlation after or during a maneuvering period, especially if no knowledge regarding the maneuvering characteristics of the target can be assumed a priori. In the context of this thesis, orbital maneuvers are classified according to the different types of space propulsion technologies, namely, chemical and electrical. The former present high-thrust magnitudes and a poor propellant utilization, whereas the latter are significantly more fuel efficient at the cost of lower thrusting forces. Nonetheless, one can derive educated guesses for the expected control magnitudes of orbital maneuvers by analyzing missions equipped with either propulsive type. These control magnitudes can be used to bound the space that is accessible (or reachable) for a target given an initial state and some temporal bounds, for instance representing the last known state and the
time elapsed since then. Still, application of these concepts requires the development of computationally efficient methods to compute orbital distances in terms of control, also known as control distance metrics, based either on chemical or electrical propulsion. In other words, a key enabler of the methodology proposed in this thesis is the development of inexpensive methods to evaluate control distance metrics, which shall capture the dynamical features of Earth’s orbital environment and the different space propulsive technologies. To this end, two different surrogate models for orbital maneuvers have been developed, under low and high-thrust assumptions, and exploited to compute not only the control distance between two orbital states but also to approximate reachability bounds conditioned on an initial state and a time of flight. Statistically consistent maneuver models are then constructed from the developed surrogates, which can provide reasonable
maneuver evidence for data association in space surveillance applications. These models are embedded in an advanced multiple maneuvering target tracking filter, capable of managing
ambiguity arising from target maneuvers, death, birth, missed sensor detections and false observations, thus being suitable for robust automated operations. Results obtained from synthetic datasets indicate the developed methods help the filter to maintain custody of maneuvering targets and resolve ambiguity in a wide range of scenarios. However, the strong dynamical impact of maneuvers leads to significant uncertainties in the state of space objects, to the point that the quality of conjunction analyses is severely degraded. Therefore, even if the developed methods are capable of maintaining custody of maneuverable space objects, it is advisable to further characterize maneuvers according to, for instance, historical data. Including heuristics in the definition of maneuver modes can help to reduce the effective uncertainty at early post-maneuver epochs, thereby increasing the overall quality of the space object catalog and allowing for accurate conjunction
analyses in the presence of maneuvering targets.El espacio orbital terrestre es un recurso natural de gran valor que ha de ser preservado.
Tanto es así que la sociedad moderna se desarrolla alrededor de multitud de servicios, la mayoría de los cuales requieren satélites en órbita terrestre. Entre ellos, cabe destacar los servicios globales de navegación por satélite y la predicción meteorológica, cruciales para la amplia mayoría de la población. Recientemente, los costes de lanzamiento y desarrollo relacionados con la industria espacial han disminuido de forma considerable, haciendo
del espacio orbital terrestre un recurso natural relativamente accesible. Aprovechando la situación, numerosas startups y universidades ahora operan satélites pequeños, de hasta media tonelada, en órbita baja. Esta clase de nuevos satélites ha de convivir con una población de objetos ya de por sí numerosa, compuesta no sólo por satélites operativos sino también por cohetes y satélites abandonados, así como fragmentos originados por
desintegraciones, explosiones y colisiones. De hecho, son estos últimos los que ponen a la comunidad espacial en alerta ya que, llegado cierto nivel de congestión en el entorno orbital, un único choque podría desencadenar una cascada de colisiones. Para evitar esta situación catastrófica, existen diversas redes de vigilancia espacial que monitorizan el espacio mediante sensores en tierra y en órbita. Los datos obtenidos a través de dichos sensores se procesan y combinan con información procedente de los operadores de
satélites para elaborar y actualizar un catálogo detallado de objetos en órbita, garantizando así cierto nivel de conocimiento acerca de la población orbital terrestre. La generación de dicho catálogo puede ayudar a prevenir futuras colisiones orbitales: mediante un análisis individualizado de las posibles conjunciones entre objetos, se pueden identificar pares de
objetos potencialmente peligrosos y así informar a los operadores de dichos objetos para que tomen las medidas pertinentes, es decir, maniobren para evitar la colisión. Realizar un seguimiento preciso de la población orbital con sensores de vigilancia es una tarea compleja, y más aún si ha de realizarse de forma autónoma. En particular, la integridad de los catálogos de objetos se ve comprometida cuando éstos realizan maniobras sin que sus operadores las reporten, ya que los sistemas de catalogación automatizados se basan
generalmente en el movimiento natural de los satélites o, a lo sumo, modelos de maniobra relativamente sencillos. Esta tesis tiene como principal objetivo avanzar en el desarrollo de herramientas y técnicas para la vigilancia y seguimiento del espacio considerando maniobras desconocidas a priori, centrándose en la definición de modelos de maniobra para objetos espaciales. Uno de los principales problemas asociados a las maniobras orbitales es la correlación de medidas, es decir, ser capaces de discernir si una observación se corresponde con un objeto que ha maniobrado recientemente. En términos generales, es complicado cuantificar la probabilidad de correlación entre una observación y un satélite que que acaba de maniobrar, más aún si se carece de información relativa a las características de maniobrabilidad del objeto en cuestión. En el contexto de esta tesis, se clasifican las maniobras orbitales en función de los distintos tipos de tecnologías de propulsión espacial (química y eléctrica). Los primeros se caracterizan por unos niveles de empuje altos y un uso ineficiente del combustible, mientras que los segundos poseen un consumo de combustible mucho más bajo que repercute en niveles de empuje relativamente pobres.
No obstante, debido a la madurez tecnológica de ambos tipos de propulsión, se pueden obtener estimaciones fundamentadas de la capacidad o magnitud de control para ambos casos, por ejemplo, analizando misiones espaciales con uno u otro tipo de motor. Dichas estimaciones pueden ser de gran utilidad para limitar el espacio accesible (o conjunto alcanzable) para un objeto dado un estado u órbita inicial y una ventana temporal, que pueden corresponderse con el último estado orbital conocido y el tiempo transcurrido
desde entonces. La aplicabilidad operativa de estos conceptos requiere de métodos computacionales (algoritmos) eficientes para calcular distancias orbitales en términos de control, también llamadas métricas de control, basadas tanto en propulsión química como eléctrica. En otras palabras, la viabilidad de la metodología propuesta en esta tesis pasa por el desarrollo de métricas de control eficientes que capturen las características dinámicas
del entorno orbital terrestre y la tecnología propulsiva utilizada en una hipotética maniobra. Con este fin, se han desarrollado dos modelos subrogados para maniobras orbitales, atendiendo a los tipos de propulsión espacial mencionados anteriormente, cuya aplicación no se limita al cálculo de distancias orbitales en términos de control si no que además pueden utilizarse para aproximar los límites del conjunto alcanzable. Dichos modelos subrogados permiten, a su vez, elaborar modelos de maniobra estadísticamente consistentes, con los que cuantificar la probabilidad de que un objeto maniobre en el proceso de correlación de medidas. Finalmente, se puede definir un sistema robusto y automatizado de vigilancia espacial mediante la incorporación de los modelos de maniobra propuestos en un filtro avanzado de seguimiento de múltiples blancos con capacidad de maniobra, capaz de gestionar no sólo la ambigüedad relativa a las maniobras per se, sino también la desaparición y nacimiento de objetos, así como falsas observaciones y detecciones omitidas por los sensores. Los resultados obtenidos en escenarios simulados indican que los métodos propuestos incrementan la capacidad actual de los sistemas de seguimiento, principalmente en lo referente al mantenimiento de custodia de objetos que
maniobran. Sin embargo, el impacto dinámico de las maniobras conlleva altos niveles de incertidumbre en el conocimiento del estado orbital de los objetos, hasta el punto de degradar la calidad de los análisis de conjunción. Por lo tanto, aunque los métodos desarrollados son capaces de realizar un seguimiento ininterrumpido de objetos con capacidad de maniobra, se recomienda caracterizar las maniobras basándose en información adicional,
tal como datos históricos. La inclusión de heurísticos de este tipo en la definición de los modos de maniobra puede ayudar a reducir de forma significativa la incertidumbre del estado en tiempos cercanos a la maniobra, incrementando de este modo la calidad del catálogo de objetos espaciales y permitiendo análisis de conjunción precisos en presencia de objetos maniobrables.Presidente: Rafael Vázquez Valenzuela. - Vocal: Kyle Jordan De Mars. - Secretario: Joaquín Míguez Arenas
- …
