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Publications (10)0 Total impact

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    ABSTRACT: The likeliest evolution of the space borne solar cell assemblies is towards thinner and lighter structures, capable to be used in combination with solar generator systems having a reduced volume at launch, combined with outstanding electrical performances.
    Photovoltaic Specialists Conference, 2008. PVSC '08. 33rd IEEE; 06/2008
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    ABSTRACT: The use of fully European triple junction (TJ) GaAs solar cell is an added value for the power generation system. Further more high efficiency TJ solar cells represent the best solution in terms of "delivered power/ mass ratio". The qualification campaigns, performed by RWE at solar cell level and by Galileo Avionica at assembly and sub-assembly level, show that all the components, material and processes used on the PVA are reliable for the ADM Aeolus mission. In the whole solar generator system design has demonstrated, during the analyses and tests phases, the ability to meet (and, in some cases, to exceed) the stringent mission requirements as long duration lifetime (high temperature long duration test on integral diode) and power demand
    Photovoltaic Energy Conversion, Conference Record of the 2006 IEEE 4th World Conference on; 06/2006
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    ABSTRACT: COSMO-SkyMed Constellation allows to use a Earth Observation Satellites System in order to guarantee peculiar operations for both commercial/civil and military applications. In this context, the EPS architecture and design have a role of utmost importance. As far as the power generation is concerned, the use of high efficiency TJ solar cells represents the best solution in terms of "delivered power/mass ratio". The qualification campaigns, performed by CESI and EMCORE at solar cell level and by Galileo Avionica at assembly and sub-assembly level, show that all the components, material and processes used on the PVA are reliable for the COSMO-SkyMed mission
    Photovoltaic Energy Conversion, Conference Record of the 2006 IEEE 4th World Conference on; 06/2006
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    ABSTRACT: The design and qualification of a reliable shunt diode device is of primary importance for all the solar array programs using GaAs triple junction (TJ) solar cells. Main issues are the sensitivity of cells to reverse bias application and their particular behaviour under reverse conditions (interaction between illumination and junction biasing). These matters impose a strong and reliable protection for every solar cell that can be implemented by means of integral diode concept. In the recent past, few diode anomalous behaviours have been detected during long duration high temperature testing: they were caused by marginal design but also by external causes like voltage and current spikes, not really representative of in-orbit conditions. Starting from these "negative" experiences, we first improved the integral diode design and then we verified by means of a comprehensive campaign all the major technical issues: on-ground and in-orbit spike environment, component rating with respect to the diode, solar cell electrical characteristics were therefore investigated and a qualification plan based on this approach was established covering all the aspects. This paper presents the diode lifetime analysis focused on spikes generator, the derating rules and finally describes all the characterization and testing activities performed for qualifying the integral by-pass device
    Photovoltaic Energy Conversion, Conference Record of the 2006 IEEE 4th World Conference on; 06/2006
  • E. Ferrando, L. Vallini
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    ABSTRACT: The market demand for earth observation satellites has increased significantly for scientific, commercial and military applications. In order to fulfil the harsh environmental requirements, typical of this type of long lasting missions (up to 5 years on orbit lifetime), Galileo Avionica have developed and qualified a comprehensive set of photovoltaic assembly (PVA) technologies. The achievements obtained so far are not only limited to the electrical parts but cover also other solar generator related issues like the substrate protection against atomic oxygen (ATOX) erosion phenomenon. The development and qualification path started from microsats solar arrays, went through a Si based large deployable solar array wing, dedicated to a 8 months mission at 350 km altitude, and arrived to the qualification of a large deployable GaAs triple junction based solar arrays for up to 5 years missions also suitable for ATOX environment. A strong support to the definition of valuable space products was also given by parallel R & D activities sponsored by the European and Italian Space Agencies.
    Photovoltaic Specialists Conference, 2005. Conference Record of the Thirty-first IEEE; 02/2005
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    ABSTRACT: Purpose of this work is the testing of materials and manufacturing processes able to withstand the high temperature conditions typical of the interplanetary space missions towards the Sun (e.g. Mercury). This goal was achieved by means of an optimisation work performed on the space solar cells already existing and "standard" photo-voltaic assembly technologies. After some preliminary tests and analyses the most suitable candidates have been identified for all the mission phases and different CICs and modules design have been established. The paper presented at the 29th PVSC conference described the preliminary trade offs and experimental activities. More than 100 CICs in various configurations and 7 modules have been manufactured to find out the best high temperature and insolation PVA concept (solar cell candidates SJ & TJ; substrate candidates: Carbon & Aluminium substrates).
    Photovoltaic Energy Conversion, 2003. Proceedings of 3rd World Conference on; 06/2003
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    ABSTRACT: The Electrical Part of the Solar Generator (EPSG) of the European Automated Transfer Vehicle (ATV) is part of the Power System of the ATV satellite, one of the main elements contributing to the International Space Station. The EPSG is installed on a deployable Solar Array composed of 4 wings; each wing is composed of 4 panels whose dimensions are 1820 /spl times/ 1150 mm/sup 2/. The layout is arranged in 2 identical sections of 3 in-parallel connected strings composed of 135 solar cells in series. The main requirements of the ATV EPSG are: to provide 1155 W @ 56.5 V per wing at SADM interface; capability to work under high angle of incidence and shadow pattern induced by the International Space Station (ISS); capability to withstand contamination environment induced by thruster plumes, material outgassing and ATOX erosion. Galileo Avionica design and manufacturing allows to meet all functional, performance and interface requirements.
    Clinical Nutrition Supplements 01/2003;
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    ABSTRACT: Purpose of this work was the selection of materials and manufacturing processes able to withstand the high temperature conditions typical of interplanetary space missions towards the Sun (e.g. Mercury). There are only few experiences reported on this subject by the scientific community. The limited time (18 months) and funding available for this study imposes a developing approach using as much as possible existing technologies. This goal is achieved by means of an optimisation work performed on the already available space solar cells and photovoltaic assembly (PVA). The studies were developed in two different paths: experiments have been carded out through tests at CIC and coupon level; analyses based on a mathematical modelling of PVA concepts to confirm the experimental data. The above led to a "high temperature and insolation" PVA baseline technology selection that is now under testing. This campaign includes tests at CIC level (single and triple-junction GaAs calls) and at coupon level (Carbon and Aluminium substrate skins) and it will be completed within the end of year 2002.
    Photovoltaic Specialists Conference, 2002. Conference Record of the Twenty-Ninth IEEE; 06/2002
  • Source
    04/2002; 502:445.
  • 01/2002;