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Berrilli F.,University of Rome Tor Vergata | Bigazzi A.,Altran GmbH | Roselli L.,University of Perugia | Sabatini P.,Carlo Gavazzi Space SpA | And 8 more authors.
Advances in Space Research | Year: 2010

ADAHELI (ADvanced Astronomy for HELIophysics) is a small-class (500 kg) low-budget (50 MEuro) satellite mission for the study of the solar photosphere and the chromosphere and for monitoring solar flare emission. ADAHELI's design has completed its Phase-A feasibility study in December 2008, in the framework of ASI's (Agenzia Spaziale Italiana) 2007 "Small Missions" Program (calling for two missions at 50 MEeuros each, plus the launch budget). ADAHELI's main purpose is to explore Sun's lower atmosphere in the near-infrared, a region so far unexplored by solar observations from space. ADAHELI will carry out observations of the solar photosphere and of the chromosphere at high-temporal rate and high spatial and spectral resolutions. ADAHELI will contribute to the understanding of Space Weather through the study of particle acceleration during flares. A radiometer operating in the millimeter radio band will continuously monitor the solar disk, throughout the spacecraft's life time. ADAHELI's baseline instruments are a 50-cm high-resolution telescope operating in the visible and the near-infrared, and a lightweight full-disk radiometer operating at millimeter wavelengths (90 GHz). The core of the telescope's focal plane suite is the spectral imager based on two Fabry-Perot interferometers, flying for the first time on a solar mission. The instrument will return fast-cadence, full bi-dimensional spectral images at high-resolution, thus improving on current slit-scan, mono-dimensional architectures. Moreover, the possibility of working in polarized light will enable full 3D magnetic field reconstruction on the photosphere and the chromosphere. An optional instrumental package is also being proposed to further extend ADAHELI's scope: a full-disk telescope for helioseismology based on a double Magneto-Optical Filter, a Neutral Particle Analyzer for magnetospheric research, an Extreme Ultraviolet imaging and spectro-radiometry instrument. These options fall outside the prescribed budget. ADAHELI, flying a Sun-Synchronous orbit at 800 km, will perform continuous, long-duration (4-h), daily acquisitions, with the possibility of extending them up to 24 h. ADAHELI's operating life is two years, plus one extension year. Launch would be nominally planned for 2014. © 2010 COSPAR.

Spadacini G.,Polytechnic of Milan | Bellan D.,Polytechnic of Milan | Pignari S.A.,Polytechnic of Milan | Grossi R.,Carlo Gavazzi Space SpA | Marliani F.,European Space Agency
2010 Asia-Pacific Symposium on Electromagnetic Compatibility, APEMC 2010 | Year: 2010

A circuit model for the prediction of conducted emissions due to DC/DC converters in a satellite power-distribution system is proposed. The noise source is represented as a linear network whose parameters are identified from measurements performed in suitable test setups. In particular: (a) the passive part of the model is represented by an admittance matrix; (b) the active part of the model is represented by ideal current sources. The cable (shielded twisted-wire pair) used to connect the DC/DC converter to the power distribution unit is characterized as a transmission line. Experimental validations confirm the effectiveness of the proposed approach. © 2010 IEEE.

Della Torre A.,Carlo Gavazzi Space SpA | Ercoli Finzi A.,Polytechnic of Milan | Genta G.,Polytechnic University of Turin | Curti F.,University of Rome La Sapienza | And 10 more authors.
Acta Astronautica | Year: 2010

The paper provides an overview of the conceptual design of the Lunar Rover conceived by Team Italia for the AMALIA Mission, candidate for the Google Lunar X Prize Challenge. The name of the mission is an acronym of the Latin language sentence "Ascensio Machinae Ad Lunam Italica Arte". With the Lunar Challenge initiative, the X Prize Foundation intends to promote the involvement of private actors in the access to space, by endowing a prize to the first privately funded lunar mission covering a certain minimum distance on the Moon surface. Additional prizes are available in case of achievement of more challenging goals, like surviving lunar night, travelling for a longer distance, visiting areas of the first Apollo Missions. Although the AMALIA Rover Subsystems are the typical ones of an Exploration Rover, their design is highly influenced by the above depicted mission context. The followed design approach is closer to the one of a commercial mission than to an Institutional Space Exploration Mission one. It has to be noted that, for being compliant with GLXP rules, at least 90% of funds required for competing in the Prize has to come from private or non-governmental sources. The achievement of such challenging goals requires adopting suitable technical and programmatic solutions, having the need to optimize costs and schedule while still maximizing the probability of success. © 2010 Elsevier Ltd. All rights reserved.

di Nicolantonio W.,Carlo Gavazzi Space SpA | Cacciari A.,Carlo Gavazzi Space SpA
Italian Journal of Remote Sensing / Rivista Italiana di Telerilevamento | Year: 2011

Aerosol satellite remote sensing can be profitably exploited in Air Quality monitoring in order to estimate the particulate matter concentration (PM) at surface level. Actually, the satellite sensor synoptic view enables monitoring of PM concentration spatial distribution fostering the analysis of the compliance with the new European Commission (EC) Directive on ambient air quality and cleaner air for Europe. In this work MODIS level 2 aerosol data are employed in a semi-empirical approach to estimate daily PM2.5 concentration at the ground over Northern Italy from 2004 to 2008. A further analysis, aimed at providing MODIS-based maps of yearly percentage of days exceeding the PM2.5 daily concentration limit prescribed by EC directive is then presented giving very promising results.

Chiarini M.,Carlo Gavazzi Space SpA | Bentini G.G.,CNR Institute for Microelectronics and Microsystems | Bianconi M.,CNR Institute for Microelectronics and Microsystems | De Nicola P.,CNR Institute for Microelectronics and Microsystems
Nuclear Instruments and Methods in Physics Research, Section B: Beam Interactions with Materials and Atoms | Year: 2010

High Energy Ion Implantation (HEII) of both medium and light mass ions has been successfully applied for the surface micromachining of single crystal LiNbO3 (LN) substrates. It has been demonstrated that the ion implantation process generates high differential etch rates in the LN implanted areas, when suitable implantation parameters, such as ion species, fluence and energy, are chosen. In particular, when traditional LN etching solutions are applied to suitably ion implanted regions, etch rates values up to three orders of magnitude higher than the typical etching rates of the virgin material, are registered. Further, the enhancement in the etching rate has been observed on x, y and z-cut single crystalline material, and, due to the physical nature of the implantation process, it is expected that it can be equivalently applied also to substrates with different crystallographic orientations. This technique, associated with standard photolithographic technologies, allows to generate in a fast and accurate way very high aspect ratio relief micrometric structures on LN single crystal surface. In this work a description of the developed technology is reported together with some examples of produced micromachined structures: in particular very precisely defined self sustaining suspended structures, such as beams and membranes, generated on LN substrates, are presented. The developed technology opens the way to actual three dimensional micromachining of LN single crystals substrates and, due to the peculiar properties characterising this material, (pyroelectric, electro-optic, acousto-optic, etc.), it allows the design and the production of complex integrated elements, characterised by micrometric features and suitable for the generation of advanced Micro Electro Optical Systems (MEOS). © 2010 Elsevier B.V. All rights reserved.

Franzoso A.,Carlo Gavazzi Space SpA | Molina M.,Carlo Gavazzi Space SpA
40th International Conference on Environmental Systems, ICES 2010 | Year: 2010

An Heat Switch, capable of self-regulation of its thermal conductance, has been developed for use on Planetary Exploration Rovers. Based on LHP technology, the Heat Switch includes a completely passive bypass valve, which can regulate the working fluid (propylene) vapour flow to the condenser, in order to prevent the evaporator temperature from falling below a given temperature set point. This allows the heat switch to cope with extremely high external temperature excursions of the outer environment and large internal power dissipation variations, still keeping a remarkable temperature stability on the controlled items and preventing their overcooling. An Heat Switch breadboard has been designed, manufactured and tested in the framework of an European Space Agency technological research programme. The activities have been successfully concluded in August 2008. The Heat Switch design and test results have been described in previous papers. This paper contains the results of the continuation of the thermal test campaign on the breadboard, which has been carried out at Carlo Gavazzi Space for more than one year in the timeframe 2008-2009. Tests have been performed both in the laboratory, at ambient temperature, and in a climatic chamber. Tests focus on those Heat Switch features which had been identified worth to be further investigated in the previous test campaign, namely the startup event and the gravity effects. Also related to the gravity effects, the valve oscillations have been investigated in detail. A large number (hundreds) of startup events has been collected, to analyze them on a statistical basis. Additional important results are the long term stability of the thermal performance parameters, the temperature control capabilities through compensation chamber heater actuation, and the detailed characterization of the condenser temperature profile at different combinations of heat loads and environmental temperatures. © 2010 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Razzano E.,Carlo Gavazzi Space SpA | Lupi T.,Carlo Gavazzi Space SpA | Sabatini P.,Carlo Gavazzi Space SpA
61st International Astronautical Congress 2010, IAC 2010 | Year: 2010

Micro-satellite platforms become the nominal solution for many Low Earth Orbit missions, due to achievable low mass, size and power, i.e. mission cost and more launch opportunities as a secondary payload. The interested applications cover several fields: Earth Observation, Science, Telecommunication, Security and Navigation. The design of a Micro-platform customizable for several missions but with a common core is of great interest, since it would permit to make the most of main bus sub-systems (On Board Computer, Power management, Attitude Control and TM/TC Transceiver) already tested and qualified, with reduced recurrent cost and time to launch. Carlo Gavazzi Space (CGS) is developing a new flexible micro-satellite platform with building-block approach distributed on two levels: the satellite itself and the equipments. Platform lifetime is up to 7 years. The satellite architecture is mainly formed by: Service Module, core of the platform and common part of the satellite; Propulsion Module, if needed, with nominal cold-gas system for orbit control; Payload Bay, interfacing the Payloads electrically and for power/data management and download. Units and equipments within the Service Module are also designed and produced in a modular way by CGS, especially The On Board Data Handling and Power Supply units, the battery and the configuration of solar panels, attitude actuators and communication transmitters. The platform software is centralized in the On Board Computer. The core has evolved in time into a multi-platform-compatible product, configurable to run on different hardware (DSP, Leon processors) and operating systems (VSPWorks, RTEMS). This paper provide a brief description of the common platform, with reference to the current on-going and planned CGS missions: the Italian MIOsat (Italian Space Agency program), a technological Earth Observation mission embarking three optical payloads; Multispectral and Panchromatic Earth Observation missions, with resolution up to 1 m, are compatible, as well as Scientific and Communication applications, like the space-based AIS system. Copyright ©2010 by the International Astronautical Federation. All rights reserved.

Fusco G.,Carlo Gavazzi Space SpA | Reulier D.,SAFT | Lo Rizzo V.,Carlo Gavazzi Space SpA
61st International Astronautical Congress 2010, IAC 2010 | Year: 2010

In recent years, starting from the success story of Agile mission, Carlo Gavazzi Space S.p.A. (CGS) in cooperation with Saft has started the development of a modular Li-ion battery for space applications. Battery modularity lies in the capability of integrating one or more basic elements named "modules" (composed of MPS 176065 cells) according to the capacity required by a specific mission. CGS-Saft modular battery can satisfy different energy requests for different satellite configurations by simply adding or removing modules, i.e. it does not need to be redesigned for each mission, minimizing development times and costs. It is worth noting that the battery modularity is both electrical and structural. CGS-Saft modular battery has been selected as energy storage unit for different ASI/ESA missions. The first flight opportunity for the modular battery is represented by the qualification flight of VEGA launcher carrying LARES system as main payload. LARES system is supplied by two independent CGS-Saft battery packs. The first one, named Avionic and Harness Battery Unit (ABU) is composed of two basic modules. The second one, named Separation Battery Unit (SBU), includes one basic module. Even if, from a functional point of view, the two battery packs (ABU and SBU) are independent, they are mounted the one next to the other composing a higher level assembly named LARES Battery. Such a solution is better from a thermal point of view and limits the waste of space on launcher mounting plate. LARES battery feeds LARES system, in order to grant the deployment of the LARES satellite (i.e. a scientific satellite for laser ranging, and of other additional micro-satellites) and the support of the VEGA qualification flight by monitoring the environmental conditions in the payload area of the launcher and by telemetering acquired data to the ground. The proto-flight model of LARES modular battery has successfully completed the manufacturing, the integration phase, and the acceptance tests including vibration, thermal, electrical, and performance tests.

Scorzolini A.,Telespazio | De Perini V.,Carlo Gavazzi Space SpA | Razzano E.,Carlo Gavazzi Space SpA | Colavolpe G.,University of Parma | And 3 more authors.
ASMS/SPSC 2010: 2010 5th Advanced Satellite Multimedia Systems Conference and the 11th Signal Processing for Space Communications Workshop | Year: 2010

A recent study of an European consortium (TPZ, Carlo Gavazzi Space, Edisoft, Elman, ITS) led by Telespazio and co-financed by ESA has investigated about the possibility of receiving AIS signals (i.e., AIS transmissions of vessels equipped with regular AIS transponders) from space with an improved performance with respect to the current literature thanks to an optimized mission design and enhanced technical capabilities mainly in terms of antennas and signal processing.The performances is assessed by means of a dedicated end-to-end System Simulator developed during the project. ©2010 IEEE.

Lorga J.F.M.,DEIMOS Engineering S.A | Silva P.F.,DEIMOS Engineering S.A | Di Cintio A.,Carlo Gavazzi Space SpA | Dovis F.,Polytechnic University of Turin | And 3 more authors.
Programme and Abstract Book - 5th ESA Workshop on Satellite Navigation Technologies and European Workshop on GNSS Signals and Signal Processing, NAVITEC 2010 | Year: 2010

The use of GNSS space receivers for autonomous orbit determination is receiving increasing interest due to the important economical and operational benefits made possible by the reduced on-ground operations and the improved pointing performance when associated to one Star Tracker. However, the exploitation of GNSS for navigating satellites in orbits beyond the GNSS constellations has not yet gained full acceptance among spacecraft designers, manufacturers and operators. With GPS modernization and upcoming Galileo as well as with evolving receiver technologies, the feasibility for the use of GNSS in geostationary and higher orbits must be thoroughly assessed as the number of factors involved and its impact on navigation performance is significant when compared to land user receivers. This paper describes the feasibility of GNSS receiver and Orbital Filter for Autonomous Orbit Determination and the main expected performances under different missions, environment and receiver architectures. The most critical factors affecting navigation performance are presented and studied in detail using a Software Simulation Tool in a dedicated test campaign. Main results of the test campaign are then presented, illustrating the achievable performances for GEO/GTO and HEO orbits under the different GNSS sensor configurations. The presented results show that the usage of GNSS receiver technologies with the advent of Galileo and GPS modernization offer new possibilities and superior performance for autonomous orbit determination, promising important economical and operational benefits for next generation of space users in either GEO or HEO orbits. ©2010 IEEE.

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