Air Mines. Urban Space Station

Air Mines The sky over the city's port was the color of a faulty screen, only partly lit up. As the silhouette of nearby buildings became darker, but more clearly visible against the fading blur-filter of a background, the realization came about how persistent a change had been taking place. Slowly, old wooden water reservoirs and rattling HVAC systems stopped being the only inhabitants of roofs. Slightly trembling, milkish jellyfish-translucent air volumes had joined the show in multiples. A few years ago artists and architects seized upon the death of buildings as their life-saving media. Equipped with constructive atlases and instruments they started disemboweling their subjects, poking about their systems, dumping out on the street the battered ugliness of their embarrassing bits and pieces, so rightly hidden by facades and height from everyday view. But, would you believe it? Even ?old ladies?, investment bankers or small children failed to get upset. Of course, old ladies are not what they used to be. It was old ladies themselves that made it happen after years of fights with the town hall, imaginative proposals and factual arguments. An industry with little financial gains but lots of welcome externalities was not, in fact, the ground for investment bankers. But they too had to admit that having otherwise stately buildings make fine particulate pencils with their facades was not the worse that could happen. Yes, making soot pencils had been found an interesting and visible end product of the endeavor, a sort of mining the air for vintage writing tools one can actually touch. The new view from the street did not seem as solid or dignified as that of old, and they hated that the market for Fine Particulates Extraction (FPE, read efpee) had to be applied on a matrix of blocks and streets that prevented undue concentration of the best or worse solutions. It had to be an evenly distributed city policy in order for the city to apply for cleaning casino money. Once the first prototypes had been deployed in buildings siding Garden Avenue or Bulwark Street even fast movers appreciated the sidekick of flower and plant smell dripping down the Urban Space Stations (USS, read use; USSs, read uses) as air and walls cooled off for a few hours after sunset. Enough. It was all nice to remember, but it was now time to go up and start the lightweight afternoon maintenance of their USS. Coop discussions had taken place all through the planning and continued through the construction phase as to how maintenance was going to be organized. Fasters had voted for a pro, pay a small amount and let them use it for rent and produce. In the end some neighbors decided they were slow enough to take care and it was now the turn. Regret came periodically, sometimes a week before, and lasted until work actually started. But lately it had been replaced by anxiety when it needed to be passed over to the next caretaker. It did not look their shift was good enough and couldn?t wait to fix it. Today small preparations needed to be made for a class visit next day from a nearby cook school. They were frequenters. It had not been easy, but it shouldn?t have been that hard. In the end, even the easiest things are hard if they involve a city, buildings and neighbors. On the face of the data, the technicalities and the way final designs had been worked out for adaptation to the different settings, the decision of where to go was self evident, but organization issues and the ever-growing politics of taste in a city of already-gentrified-rodents almost put the project in the frozen orbit of timeless beautiful future possibilities. This is how it was. A series of designs by XClinic and OSS had made it possible to adapt to different building structures, leave in most cases the roof untouched and adapted a new technology of flexing fiberglass tubes that dissipated wind pressure in smooth bending.......

Dynamic stabilization of L2 periodic orbits using attitude-orbit coupling effects

Numerical explorations show how the known periodic solutions of the Hill problem are modified in the case of the attitude-orbit coupling that may occur for large satellite structures. We focus on the case in which the elongation is the dominant satellite’s characteristic and find that a rotating structure may remain with its largest dimension in a plane parallel to the plane of the primaries. In this case, the effect produced by the non-negligible physical length is dynamically equivalent to the perturbation produced by an oblate central body on a mass-point satellite. Based on this, it is demonstrated that the attitude-orbital coupling of a long enough body may change the dynamical characteristics of a periodic orbit about the collinear Lagrangian points.

Comparative characterization of dietary fibre-Enriched Frozen/thawed mashed potatoes

The potential use of commercial fibres (pea fibre, inulin, and their blends), as fibre-enriching agents in frozen/thawed mashed potatoes was reported. Pea fibre and inulin supplementations conferred hardness and softness to the product, respectively. Differences were attributed to the relationship of the fibre with the potato starch matrix. The association of pea fibre at low concentration (<15 g/kg mashed potatoes) and inulin at high concentration (>45 g/kg) is strongly encouraged to fortify the diet without promoting negative effects on textural and rheological properties of frozen/thawed mashed potatoes or colour and overall acceptability of the resulting products.

Adaptive scheme for Accurate orbit propagation

Two extensions of the fast and accurate special perturbation method recently developed by Peláez et al. are presented for respectively elliptic and hyperbolic motion. A comparison with Peláez?s method and with the very efficient Stiefel- Scheifele?s method, for the problems of oblate Earth plus Moon and continuous radial thrust, shows that the new formulations can appreciably improve the accuracy of Peláez?s method and have a better performance of Stiefel-Scheifele?s method. Future work will be to include the two new formulations and the original one due to Peláez into an adaptive scheme for highly accurate orbit propagation

Dynamic stabilization of L2 periodic orbits using attitude-orbit coupling effects

Numerical explorations show how the known periodic solutions of the Hill problem are modified in the case of the attitude-orbit coupling that may occur for large satellite structures. We focus on the case in which the elongation is the dominant satellite?s characteristic and find that a rotating structure may remain with its largest dimension in a plane parallel to the plane of the primaries. In this case, the effect produced by the non-negligible physical dimension is dynamically equivalent to the perturbation produced by an oblate central body on a masspoint satellite. Based on this, it is demonstrated that the attitude-orbital coupling of a long enough body may change the dynamical characteristics of a periodic orbit about the collinear Lagrangian points.

Frozen orbits for scientific missions using rotating tethers

We derive a semi-analytic formulation that permits to study the long-term dynamics of fast-rotating inert tethers around planetary satellites. Since space tethers are extensive bodies they generate non-keplerian gravitational forces which depend solely on their mass geometry and attitude, that can be exploited for controlling science orbits. We conclude that rotating tethers modify the geometry of frozen orbits, allowing for lower eccentricity frozen orbits for a wide range of orbital inclination, where the length of the tether becomes a new parameter that the mission analyst may use to shape frozen orbits to tighter operational constraints.

The radiation impedance of electrodynamics tethers in a polar Jovian orbit

Juno, the second mission in the NASA New Frontiers Program, will both be a polar Jovian orbiter, and use solar arrays for power, moving away from previous use of radioisotope power systems (RPSs) in spite of the weak solar light reaching Jupiter. The power generation at Jupiter is critical, and a conductive tether could be an alternative source of power. A current-carrying tether orbiting in a magnetized ionosphere/plasmasphere will radiate waves. A magnitude of interest for both power generation and signal emission is the wave impedance. Jupiter has the strongest magnetic field in the Solar Planetary System and its plasma density is low everywhere. This leads to an electron plasma frequency smaller than the electron cyclotron frequency, and a high Alfven velocity. Unlike the low Earth orbit (LEO) case, the electron skin depth and the characteristic size of plasma contactors affect the Alfven impedance.

Analysis of bare-tether systems for deorbiting low-earth-orbit satellites

Performances, design criteria, and system mass of bare tethers for satellite deorbiting missions are analyzed. Orbital conditions and tether cross section define a tether length, such that 1) shorter tethers are electron collecting practically in their whole extension and 2) longer tethers collect practically the short-circuit current in a fixed segment length. Long tethers have a higher drag efficiency (defined as the drag force vs the tether mass) and are better adapted to adverse plasma densities. Dragging efficiency and mission-related costs are used to define design criteria for tether geometry. A comparative analysis with electric thrusters shows that bare tethers have much lower costs for low- and midinclination orbits and remain an attractive option up to 70 deg.

An universal system to de-orbit satellites at end of life

A 3-year Project financed by the European Commission is aimed at developing a universal system to de-orbit satellites at their end of life, as a fundamental contribution to limit the increase of debris in the Space environment. The operational system involves a conductive tapetether left bare to establish anodic contact with the ambient plasma as a giant Langmuir probe. The Project will size the three disparate dimensions of a tape for a selected de-orbit mission and determine scaling laws to allow system design for a general mission. Starting at the second year, mission selection is carried out while developing numerical codes to implement control laws on tether dynamics in/off the orbital plane; performing numerical simulations and plasma chamber measurements on tether-plasma interaction; and completing design of subsystems: electronejecting plasma contactor, power module, interface elements, deployment mechanism, and tether-tape/end-mass. This will be followed by subsystems manufacturing and by currentcollection, free-fall, and hypervelocity impact tests.

Electrodynamic tether for scientific mission in low Jovian orbit

An electrodynamic bare tether is shown to allow carrying out scientific observations very close to Jupiter, for exploration of its surface and subsurface, and ionospheric and atmospheric in-situ measurements. Starting at a circular equatorial orbit of radius about 1.3/1.4 times the Jovian radius, continuous propellantless Lorentz drag on a thin-tape tether in the 1-5 km length range would make a spacecraft many times as heavy as the tape slowly spiral in, over a period of many months, while generating power at a load plugged in the tether circuit for powering instruments in science data acquisition and transmission. Lying under the Jovian radiation belts, the tape would avoid the most severe problem facing tethers in Jupiter, which are capable of producing both power and propulsion but, operating slowly, could otherwise accumulate too high a radiation dose . The tether would be made to spin in its orbit to keep taut; how to balance the Lorentz torque is discussed. Constraints on heating and bowing are also discussed, comparing conditions for prograde versus retrograde orbits. The system adapts well to the moderate changes in plasma density and motional electric field through the limited radial range in their steep gradients near Jupiter.

Trade-off study on deorbiting S/C in near polar orbit

Usual long, flexible, ED tethers kept vertical by the gravity gradient might be less efficient for deorbiting S/C in near-polar orbits than conventional (Hall, Ion) electrical thrusters. A trade-off study on this application is here presented for tethers kept horizontal and perpendicular to the orbital plane. A tether thus oriented must be rigid and short for structural reasons, requiring a non-convex cross section and a power supply as in the case of electrical thrusters. Very recent developments on bare-tether collection theory allow predicting the current collected by an arbitrary cross section. For the horizontal tether, structural considerations on length play the role of ohmic effects in vertical tethers, in determining the optimal contribution of tether mass to the overall deorbiting system. For a given deorbiting-mission impulse, tether-system mass is minimal at some optimal length that increases weakly with the impulse. The horizontal-tether system may beat both the vertical tether and the electrical thruster as regards mass requirements for a narrow length range centered at about 100 m, allowing, however, for a broad mission-impulse range.

Saturn power generation with electrodynamic tethers in polar orbit

A power generation scheme based on bare electrodynamic tethers (EDT), working in passive mode is investigated for the purpose of supplying power to scientific missions at Saturn. The system employs a spinning EDT on a lowaltitude polar orbit which permits to efficiently convert plasmasphere energy into useful power. After optimizing the tether design for power generation we compute the supplied power along the orbit and the impact of the Lorentz force on the orbital elements as function of the tether and orbit characteristics. Although uncertainties in the current ionosphere density modeling strongly affect the performance of the system the peak power density of the EDT appears be greater than conventional power systems.

Diseño y ensayos en tierra de paneles solares para un satélite de órbita baja = Design and testing procedures of a Low Earth Orbit (LEO) satellite solar panels

Debido al reciente incremento de conflictos en el mundo árabe y dado el interés nacional de España en dicha zona, se propone en este proyecto un estudio inicial para el diseño y desarrollo de un microsatélite que ayude al gobierno de España a mantener esa zona bajo observación constante. En el presente trabajo se abarcan todos los subsistemas del satélite, haciéndose un estudio más detallado del subsistema de potencia

Diseño del sistema de potencia para un satélite de órbita baja(LEO) = Design of a Low Earth Orbit (LEO) satellite power subsystem

Este documento contiene el proceso de prediseño y cálculo de un satélite de observación terrestre mediante imágenes fotográficas. El principal objetivo del proyecto es el diseño detallado del subsistema de potencia del satélite y a validación de un modelo de funcionamiento del sistema de potencia de las placas solares que alimentan al mismo y mediante la herramienta Simulink. La primera parte consiste en un diseño breve de los subsistemas y parámetros más importantes del satélite tales como el Sistema de Control de Actitud, Sistema de Control Térmico y Sistema de Comunicaciones, además de la estructura del satélite, la órbita en la que se encontrará, el lanzador que se usará para situarlo en órbita y la cámara que llevara a bordo para la captación de imágenes. La segunda parte trata del diseño del subsistema de potencia de una manera más detallada y de su simulación mediante una herramienta diseñada en el programa MATLAB con la herramienta Simulink. Se pretende usar la herramienta para simular el comportamiento del subsistema de potencia de un satélite conocido que será el UPMSat-2.

Diseño y ensayos en tierra de las baterías para un satélite de órbita baja = Design and testing procedures of a Low Earth Orbit (LEO) satellite battery

Este proyecto consiste en el estudio y dimensionado inicial del sistema de potencia de un satélite de observación, que sirva de ayuda a otros sistemas de mayor precisión a la hora de detectar posibles terremotos y actividad volcánica mediante el análisis de señales electromagnéticas presentes en la ionosfera. Para ello el satélite incorpora, entre otros elementos sensores eléctricos, un analizador de plasma, y un detector de partículas. Con esta instrumentación se pretenden detectar los cambios que se producen en el campo electromagnético terrestre como consecuencia del movimiento de las placas tectónicas, y descubrir así las posibles anomalías que preceden a un seísmo. Para no sobrepasar el presupuesto con el que se ha ideado el proyecto se utilizarán sistemas que permitan la lectura de datos de la forma más simple, pudiendo ocurrir que los datos recogidos no se transmitan al control de Tierra en tiempo real, impidiendo a los científicos analizar los datos recogidos hasta unos días después, de ahí que este satélite experimental deba emplearse, en principio, como apoyo a programas de detención de terremotos más sofisticados y con mayores medios técnicos. Evidentemente, con este sistema también se podrán recoger datos tras los seísmos y examinarlos posteriormente. La órbita del satélite será una órbita LEO (Low Earth Orbit) de una altitud aproximada de 670 Km, estimándose el tiempo de vida del satélite en 5 años. Intentando emplear la mayor parte de los recursos económicos en el equipamiento científico, la estructura será la más simple posible, esto es, un paralelepípedo de dimensiones compactas con un peso aproximado de 185 kg, contando con paneles solares desplegables y en su interior con baterías que proporcionarán potencia al satélite durante la fase de lanzamiento y en momentos concretos.