Solution of optimal continuous low-thrust transfer using Lie transforms

This paper addresses the problem of optimal constant continuous low-thrust transfer in the context of the restricted two-body problem (R2BP). Using the Pontryagin’s principle, the problem is formulated as a two point boundary value problem (TPBVP) for a Hamiltonian system. Lie transforms obtained through the Deprit method allow us to obtain the canonical mapping of the phase flow as a series in terms of the order of magnitude of the thrust applied. The reachable set of states starting from a given initial condition using optimal control policy is obtained analytically. In addition, a particular optimal transfer can be computed as the solution of a non-linear algebraic equation. Se investiga el uso de series y transformadas de Lie en problemas de optimización de trayectorias de satélites impulsados por motores de bajo empuje

Prospecto de la Encyclopedia metodica : [Texto impreso] por orden de materias

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Confutatio demonstrationis typis editae ac Petro Morata in publica concertatione pro Phil. Cath. [Texto impreso]

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DROMO formulation for planar motions: Solution to the Tsien Problem

The two-body problem subject to a constant radial thrust is analyzed as a planar motion. The description of the problem is performed in terms of three perturbation methods: DROMO and two others due to Deprit. All of them rely on Hansen?s ideal frame concept. An explicit, analytic, closed-form solution is obtained for this problem when the initial orbit is circular (Tsien problem), based on the DROMO special perturbation method, and expressed in terms of elliptic integral functions. The analytical solution to the Tsien problem is later used as a reference to test the numerical performance of various orbit propagation methods, including DROMO and Deprit methods, as well as Cowell and Kustaanheimo?Stiefel methods.

Singularities in DROMO formulation. Analysis of deep flybys

The singularities in Dromo are characterized in this paper, both from an analytical and a numerical perspective. When the angular momentum vanishes, Dromo may encounter a singularity in the evolution equations. The cancellation of the angular momentum occurs in very speci?c situations and may be caused by the action of strong perturbations. The gravitational attraction of a perturbing planet may lead to rapid changes in the angular momentum of the particle. In practice, this situation may be encountered during deep planetocentric ?ybys. The performance of Dromo is evaluated in di?erent scenarios. First, Dromo is validated for integrating the orbit of Near Earth Asteroids. Resulting errors are of the order of the diameter of the asteroid. Second, a set of theoretical ?ybys are designed for analyzing the performance of the formulation in the vicinity of the singularity. New sets of Dromo variables are proposed in order to minimize the dependency of Dromo on the angular momentum. A slower time scale is introduced, leading to a more stable description of the ?yby phase. Improvements in the overall performance of the algorithm are observed when integrating orbits close to the singularity.

La Unificación de la Física

Aunque a lo largo de la historia de la Física hemos avanzado construyendo una serie de teorías parciales que expliquen diferentes fenómenos de nuestra naturaleza aparentemente independientes entre sí, sería muy difícil construir en un solo paso una teoría unificada completa de todo lo que ocurre en el universo. En este trabajo presentamos un breve resumen de la evolución de las diferentes teorías parciales y el intento de unificación por parte de la comunidad científica de todas esas teorías en la denominada Teoría del Todo.

Estado de la astronomia en Europa [Texto impreso] : Y juicio de los fundamentos sobre que se erigieron los Systemas del Mundo, para que sirva de guia al mètodo en que debe recibirlos la Nación ...

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Magnetic Attitude Control for Satellites in Polar or Sun-Synchronous Orbits

In this work, a new law for magnetic control of satellites in near-polar orbits is presented. This law has been developed for the UMPSat-2 microsatellite, which has been designed and manufactured by Universidad Politécnica de Madrid, Madrid. The control law is a modification of the B-dot strategy that enables the satellite to control the rotation rate. Besides, the satellite?s equilibrium state is characterized by having the rotation axis perpendicular to the orbit?s plane. The control law described in the present work only needs magnetometers and magnetorquers, as sensors and actuators, respectively, to carry out a successful attitude control on the spacecraft. A description of the analysis is included. Performance and applicability of the proposed method have been demonstrated by control dynamics together with Monte Carlo techniques and by implementing the control law in the UPMSat-2 mission simulator. Results show good performance in terms of acquisition and stability of the satellite rotation rate and orientation with respect to its orbit?s plane.

Lock-in amplifiers for AMR sensors

Anisotropic magnetoresistive (AMR) magnetic sensors are often chosen as the magnetic transducer for magnetic field sensing in applications with low to moderate magnetic field resolution because of the relative low mass of the sensor and their ease of use. They measure magnetic fields in the order of the Earth magnetic field (with typical sensitivities of 1‰/G or 10−2‰/μT), have typical minimum detectable fields in order of nT and even 0.1 nT but they are seriously limited by the thermal drifts due to the variation of the resistivity with temperature (∼2.5‰/°C) and the variation of the magnetoresistive effect with temperature (which affects both the sensitivity of the sensors: ∼2.7‰/°C, and the offset: ±0.5‰/°C). Therefore, for lower magnetic fields, fluxgate vector sensors are generally preferred. In the present work these limitations of AMR sensors are outlined and studied. Three methods based on lock-in amplifiers are proposed as low noise techniques. Their performance has been simulated, experimentally tested and comparatively discussed. The developed model has been also used to derive a technique for temperature compensation of AMR response. The final goal to implement these techniques in a space qualified applied specific integrated circuit (ASIC) for Mars in situ exploration with compact miniaturized magnetometers.

Estimación de parámetros de propagación atmosférica en ausencia de lluvia utilizando escalado en frecuencias y otras técnicas

Las comunicaciones por satélite tienen cada vez mayores necesidades de espectro, con el objetivo de ofrecer servicios de banda ancha, tanto de comunicación de datos como de radiodifusión. En esta línea, se está incrementando de manera importante el uso de frecuencias en la banda Ka (20 y 30 GHz), que se verá complementada en el futuro por la banda Q/V (40 y 50 GHz) y por frecuencias en la banda W (por encima de 60 GHz). En estas frecuencias, microondas y ondas milimétricas, la troposfera produce importantes efectos de propagación. El más estudiado es el efecto de la lluvia, que produce desvanecimientos muy profundos. Sin embargo, la lluvia está presente en porcentajes de tiempo pequeños, típicamente inferiores al 5% en los climas templados. El resto del tiempo, más del 95% por ejemplo en los climas mencionados, los gases y las nubes pueden causar niveles importantes de atenuación en estas frecuencias. La Tesis aporta un nuevo modelo (Modelo Lucas-Riera), consistente en un conjunto de polinomios de aproximación para realizar, en ausencia de lluvia, la estimación de determinados parámetros de propagación, partiendo de otros datos que se suponen disponibles. El modelo está basado en datos obtenidos de radiosondeos meteorológicos y modelos físicos de atenuación por gases y nubes, que son los fenómenos más relevantes en ausencia de lluvia, y tiene en cuenta las características climatológicas del emplazamiento de interés, utilizando la clasificación climática de Köppen. Este modelo es aplicable en las bandas de frecuencias entre 12 y 100 GHz (exceptuando 60 GHz), donde se aproximarían los mencionados parámetros de propagación en una frecuencia a partir de los obtenidos en otra, en el caso de la atenuación y la temperatura de brillo, o bien se estimaría la temperatura media de radiación a una determinada frecuencia partiendo de la temperatura de superficie. Con este modelo se puede obtener una aproximación razonable si se conoce la Zona Climática de Köppen de la localización terrestre para la que queremos calcular las aproximaciones y en caso de que ésta se desconozca se aporta una Zona Global, que representa toda la superficie terrestre. La aproximación que se propone para realizar el escalado en frecuencia puede ser útil en los enlaces de comunicaciones por satélite, en los que a menudo se dispone de información en relación a los parámetros de propagación a una determinada frecuencia, por ejemplo en el enlace descendente, y sería de utilidad conocer esos mismos parámetros en el enlace ascendente de cara a poder mitigar los efectos que tiene la atmósfera sobre la señal emitida (atenuación, desvanecimiento, etc). En el caso de la temperatura media de radiación, la aproximación que se propone podría ser útil de cara a la realización de medidas de radiometría, diseño de equipamiento de instrumentación o comunicaciones por satélite.

Thermal control of SUNRISE, a balloon-borne solar telescope

SUNRISE is a balloon-borne solar telescope flown with a long-duration balloon by NASA's Columbia Scientific Balloon Facility team from Esrange (Swedish Space Corporation), on 8 June 2009. SUNRISE has been a challenging mission from the thermal point of view because of its size and power dissipation. Thus, a dedicated thermal analysis has been carried out to find a solution that allows all the devices to be kept within their appropriate temperature ranges, without exceeding the allowable temperature gradients, critical for optical devices. In this article, the thermal design of SUNRISE is described. A geometrical mathematical model and a thermal mathematical model of the whole system have been set up for the different load cases in order to obtain the temperature distribution and gradients in the system. Some trade-offs have been necessary to fulfil all the thermal requirements. The thermal hardware used to achieve it is described. Finally, the temperatures obtained with the models have been compared with flight data.

Observations of Comet 9P/Tempel 1 around the Deep Impact event by the OSIRIS cameras onboard Rosetta

The OSIRIS cameras on the Rosetta spacecraft observed Comet 9P/Tempel 1 from 5 days before to 10 days after it was hit by the Deep Impact projectile. The Narrow Angle Camera (NAC) monitored the cometary dust in 5 different filters. The Wide Angle Camera (WAC) observed through filters sensitive to emissions from OH, CN, Na, and OI together with the associated continuum. Before and after the impact the comet showed regular variations in intensity. The period of the brightness changes is consistent with the rotation period of Tempel 1. The overall brightness of Tempel 1 decreased by about 10% during the OSIRIS observations. The analysis of the impact ejecta shows that no new permanent coma structures were created by the impact. Most of the material moved with View the MathML source∼200ms−1. Much of it left the comet in the form of icy grains which sublimated and fragmented within the first hour after the impact. The light curve of the comet after the impact and the amount of material leaving the comet (View the MathML source4.5–9×106kg of water ice and a presumably larger amount of dust) suggest that the impact ejecta were quickly accelerated by collisions with gas molecules. Therefore, the motion of the bulk of the ejecta cannot be described by ballistic trajectories, and the validity of determinations of the density and tensile strength of the nucleus of Tempel 1 with models using ballistic ejection of particles is uncertain.

Sonic anemometry of planetary atmospheres

The application of a recently developed model of sonic anemometers measuring process has revealed that these sensors cannot be considered as absolute ones when measuring spectral characteristics of turbulent wind speed since it is demonstrated that the ratios of measured to real spectral density functions depend on the composition and temperature of the considered planetary atmosphere. The new model of the measuring process of sonic anemometers is applied to describe the measuring characteristics of these sensors as fluid/flow dependent (against the traditional hypothesis of fluid/flow independence) and hence dependent on the considered planetary atmosphere. The influence of fluid and flow characteristics (quantified via the Mach number of the flow) and the influence of the design parameters of sonic anemometers (mainly represented by time delay between pulses shots and geometry) on turbulence measurement are quantified for the atmospheres of Mars, Jupiter, and Earth. Important differences between the behavior of these sensors for the same averaged wind speed in the three considered atmospheres are detected in terms of characteristics of turbulence measurement as well as in terms of optimum values of anemometer design parameters for application on the different considered planetary atmospheres. These differences cannot be detected by traditional models of sonic anemometer measuring process based on line averaging along the sonic acoustic paths.

The experiment CPLM (comportamiento de puentes líquidos en microgravedad) on board Minisat 01

The Universidad Politécnica de Madrid participates in the MINISAT 01 program as the experiment CPLM responsible. This experiment aims at the study of the fluid behaviour in reduced gravity conditions. The interest of this study is and has been widely recognised by the scientific community and has potential applications in the pharmaceutical and microelectronic technologies (crystal growth), among others. The scientific team which has developed the CPLM experiment has a wide experience in this field and had participate in the performance of a large number of experiments on the fluid behaviour in reduced gravity conditions in flight (Spacelab missions, TEXUS sounding rockets, KC-135 and Caravelle aeroplanes, drop towers, as well as on earth labs (neutralbuoyancy and small scale simulations). The experimental equipment used in CPLMis a version of the payload developed for experimentation on drop towers and on board microsatellites as the UPM-Sat 1, adapted to fly on board MINISAT 01.

Osiris— The optical, spectroscopic and infrared remote imaging system for the Rosetta orbiter

The scientific objectives, design, and implementation of the Optical, Spectroscopic, and Infrared Remote Imaging System (OSIRIS) for the International Rosetta Mission are described. The instrument comprises two camera systems with a common electronics box. A narrow angle camera will provide high resolution images of the structure and morphology of the nucleus of a comet. A wide angle camera with high straylight rejection and dynamic range will be used to investigate the innermost coma and the emission process at the surface of the comet. An infrared imaging system, which dramatically enhances the scientific return has been included in the narrow angle camera at little extra cost.