IAA : Información y actualidad astronómica (39)

Sumario : La evolución química del universo.-- Supervientos galácticos.-- CIENCIA EN HISTORIAS. Williamina Patton Fleming. De criada a astrónoma.-- DECONSTRUCCIÓN Y otros ENSAYOS. El bosón de Higgs.-- EL “MOBY DICK” DE... Begoña Ascaso (IAA-CSIC).-- ACTUALIDAD.-- ENTRE BASTIDORES.-- SALA LIMPIA.-- CIENCIA: PILARES E INCERTIDUMBRES. Veinte años de cinturón transneptuniano.N

SINBAD electronic models of the interface and control system for the NOMAD spectrometer on board of ESA ExoMars Trace Gas Orbiter mission

NOMAD is a spectrometer suite: UV-visible-IR spectral ranges. NOMAD is part of the payload of ESA ExoMars Trace Gas Orbiter Mission. SINBAD boards are in charge of the communication and management of the power and control between the spacecraft and the instrument channels. SINBAD development took four years, while the entire development and test required five years, a very short time to develop an instrument devoted to a space mission. The hardware of SINBAD is shown in the attached poster: developed boards, prototype boards and final models. The models were delivered to the ESA in order to testing and integration with the spacecraft

SINBAD flight software, the on board software of NOMAD in ExoMars 2016

The Spacecraft INterface and control Board for NomAD (SINBAD) is an electronic interface designed by the Instituto de Astroffisica de Andalucfia (IAA-CSIC). It is part of the Nadir and Occultation for MArs Discovery instrument (NOMAD) on board in the ESAs ExoMars Trace Gas Orbiter mission. This mission was launched in March 2016. The SINBAD Flight Software (SFS) is the software embedded in SINBAD. It is in charge of managing the interfaces, devices, data, observing sequences, patching and contingencies of NOMAD. It is presented in this paper the most remarkable aspects of the SFS design, likewise the main problems and lessons learned during the software development process

Monitoring and predicting the risk of violence in residential facilities. No difference between patients with history or with no history of violence

none34noopende Girolamo, Giovanni; Buizza, Chiara; Sisti, Davide; Ferrari, Clarissa; Bulgari, Viola; Iozzino, Laura; Boero, Maria Elena; Cristiano, Giuseppe; De Francesco, Alessandra; Giobbio, Gian Marco; Maggi, Paolo; Rossi, Giuseppe; Segalini, Beatrice; Candini, Valentina; Andreose, Suor; Basso, Pasquale; Beneduce, Rossella; Bertolotti, Pietro; Braida, Vanda; Bonelli, Marina; Bongiorno, Fanny; Bussi, Riccardo; Castagno, Elisa; Dominicis, Fabio; Ghersi, Loredana; Greppo, Stefania; Sodano, Alessandro Jaretti; Leporatti, Massimo; Presti, Eleonora Lo; Milone, Valeria; Panigada, Fausto; Pasquadibisceglie, Livia; Rigamonti, Danilo; Rillosi, Lucianade Girolamo, Giovanni; Buizza, Chiara; Sisti, Davide; Ferrari, Clarissa; Bulgari, Viola; Iozzino, Laura; Boero, Maria Elena; Cristiano, Giuseppe; De Francesco, Alessandra; Giobbio, Gian Marco; Maggi, Paolo; Rossi, Giuseppe; Segalini, Beatrice; Candini, Valentina; Andreose, Suor; Basso, Pasquale; Beneduce, Rossella; Bertolotti, Pietro; Braida, Vanda; Bonelli, Marina; Bongiorno, Fanny; Bussi, Riccardo; Castagno, Elisa; Dominicis, Fabio; Ghersi, Loredana; Greppo, Stefania; Sodano, Alessandro Jaretti; Leporatti, Massimo; Presti, Eleonora Lo; Milone, Valeria; Panigada, Fausto; Pasquadibisceglie, Livia; Rigamonti, Danilo; Rillosi, Lucian

Development of a miniaturized real time attitude control system for nano and microsatellites

Microsatelliti e nanosatelliti, come ad esempio i Cubesat, sono carenti di sistemi integrati di controllo d’assetto e di manovra orbitale. Lo scopo di questa tesi è stato quello di realizzare un sistema compatibile con Cubesat di una unità, completo di attuatori magnetici e attuatori meccanici, comprendente tutti i sensori e l’elettronica necessaria per il suo funzionamento, creando un dispositivo totalmente indipendente dal veicolo su cui è installato, capace di funzionare sia autonomamente che ricevendo comandi da terra. Nella tesi sono descritte le campagne di simulazioni numeriche effettuate per validare le scelte tecnologiche effettuate, le fasi di sviluppo dell’elettronica e della meccanica, i test sui prototipi realizzati e il funzionamento del sistema finale. Una integrazione così estrema dei componenti può implicare delle interferenze tra un dispositivo e l’altro, come nel caso dei magnetotorquer e dei magnetometri. Sono stati quindi studiati e valutati gli effetti della loro interazione, verificandone l’entità e la validità del progetto. Poiché i componenti utilizzati sono tutti di basso costo e di derivazione terrestre, è stata effettuata una breve introduzione teorica agli effetti dell’ambiente spaziale sull’elettronica, per poi descrivere un sistema fault-tolerant basato su nuove teorie costruttive. Questo sistema è stato realizzato e testato, verificando così la possibilità di realizzare un controller affidabile e resistente all’ambiente spaziale per il sistema di controllo d’assetto. Sono state infine analizzate alcune possibili versioni avanzate del sistema, delineandone i principali aspetti progettuali, come ad esempio l’integrazione di GPS e l’implementazione di funzioni di determinazione d’assetto sfruttando i sensori presenti a bordo.Microsatellites and nanosatellites, such as Cubesat, usually lack of integrated orbital maneuver and attitude control systems. The aim of this thesis has been to realize a control system compatible with 1U Cubesat, integrating magnetic control, mechanical actuators and all needed sensors and electronics for their functioning, creating a device fully independent from the hosting spacecraft, capable to both autonomous and ground controlled operations. In this thesis the numerical simulation campaigns to validate the technical choices are described, together with the development of the electronics and mechanical structure, with the prototype tests and the final system characteristics. Such extreme integration may generate interferences between different devices, such as magnetotorquer and magnetometers. These effects have been studied and evaluated, verifying their amplitude and the validity of the design. Since the project is based on off-the-shelf components and ground electronics, after a brief theoretical introduction on space effects on electronic components, a fault-tolerant system based on newly developed theories has been described. This system has been designed, built and tested, verifying the possibility to realize a reliable digital controller for the attitude control system capable to resist to the space environment. Some advance versions of the control system have also been defined, describing the main characteristics, such as an integrated GPS or the implementation of attitude determination functions using the onboard sensors

Miniaturized attitude control system for nanosatellites

A miniaturized attitude control system suitable for nanosatellites, developed using only commercial off-the-shelf components, is described in the paper. It is a complete and independent system to be used on board nanosatellites, allowing automated attitude control. To integrate this system into nanosatellites such as Cubesats its size has been reduced down to a cube of side about 5 cm. The result is a low cost attitude control system built with terrestrial components, integrating three micro magnetotorquers, three micro reaction wheels, three magnetometers and redundant control electronics, capable of performing automatics operations on request from the ground. The system can operate as a real time maneuvering system, executing commands sent from the ground or as a standalone attitude control system receiving the solar array status from a hosting satellite and the satellite ephemeris transmitted from the ground station. The main characteristics of the developed system and test results are depicted in this paper. (C) 2012 Elsevier Ltd. All rights reserved

Design and manufacture of a low cost educational hexapod rover

The paper deals with the design and realization of a hexapod rover prototype completely manufactured by students and researchers of the Space Robotics Group of the II Faculty of Engineering of the University of Bologna “ALMA MATER”. The rover project has been developed for didactical purposes, with the aim of involving students in practical, hands-on education, pushing them to face real problems and to put in practice what they have learnt in theory during regular courses. The work done is described in the paper, highlighting its potential to test different solutions in autonomous navigation systems: low-cost sensors, innovative algorithms and different step procedures. Moreover, the mechanical and electronic solutions adopted for leg design, main controller, and remote control are discussed and depicted in the paper

Design, Manufacturing, and Test of a Real-Time, Three-Axis Magnetic Field Simulator

This paper deals with the design, manufacturing, and test of a three-axis magnetic field simulator for space applications. The main aim of this simulator is to reproduce the orbital magnetic field conditions in a definite volume. The simulator makes it possible to carry out the ground calibration campaign of the satellite magnetic sensors and can be used in attitude control system simulations that exploit "hardware in the loop" devices. An overview of the mechanical and electronics design of the system is given; the mathematical model of the expected field is also discussed, achieving design constraints to get the largest homogeneous magnetic field volume. Moreover, test campaign results regarding magnetic field homogeneity are depicted and compared with those expected in theory

An orientable solar panel system for nanospacecraft

An orientable deployed solar array system for 1-5 kg weight nanospacecraft is described, enhancing the achievable performance of these typically power-limited systems. The system is based on a deployable solar panel system, previously developed with cooperation between Laboratorio di Sistemi Aerospaziali of University of Roma "la Sapienza" and the company IMT (Ingegneria Marketing Tecnologia). The system proposed is a modular one, and suitable in principle for the 1U, 2U and 3U standard Cubesat bus, even if the need for three axis attitude stabilization makes it typically preferred for 3U Cubesats. The size of each solar panel is the size of a lateral Cubesat surface. A single degree of freedom maneuvering capability is given to the deployed solar array, in order to follow the apparent motion of the sun as close as possible, given the mission requirements on the spacecraft attitude. Considerable effort has been devoted to design the system compatible with the Cubesat standard, being mounted outside on the external spacecraft structure, without requiring modifications on the standard prescriptions. The small available volume is the major constraint, which forces to use miniaturized electric motor technology. The system design trade-off is discussed, leading to the selection of an architecture based on two independently steerable solar array wings. (C) 2014 IAA. Published by Elsevier Ltd. All rights reserved