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Padova, Italy

Bombardelli C.,Technical University of Madrid | Bau G.,CISAS | Pelaez J.,Technical University of Madrid
Celestial Mechanics and Dynamical Astronomy | Year: 2011

An analytical solution of the two body problem perturbed by a constant tangential acceleration is derived with the aid of perturbation theory. The solution, which is valid for circular and elliptic orbits with generic eccentricity, describes the instantaneous time variation of all orbital elements. A comparison with high-accuracy numerical results shows that the analytical method can be effectively applied to multiple-revolution low-thrust orbit transfer around planets and in interplanetary space with negligible error. © 2011 Springer Science+Business Media B.V. Source


Molfese C.,National institute for astrophysics | Schipani P.,National institute for astrophysics | Marty L.,National institute for astrophysics | Esposito F.,National institute for astrophysics | And 8 more authors.
2014 IEEE International Workshop on Metrology for Aerospace, MetroAeroSpace 2014 - Proceedings | Year: 2014

This paper describes the Electrical Ground Support Equipment (EGSE) developed for automatic tests of DREAMS (Dust characterization, Risk assessment, and Environment Analyser on the Martian Surface), that is the only surface payload package to be accommodated on the Entry, Descendent and landing Module (EDM) of the ExoMars 2016 mission to Mars, developed by the European Space Agency (ESA) in collaboration with the Russian Federal Space Agency (Roscosmos). © 2014 IEEE. Source


Molfese C.,National institute for astrophysics | Schipani P.,National institute for astrophysics | Marty L.,National institute for astrophysics | Esposito F.,National institute for astrophysics | And 9 more authors.
Proceedings of SPIE - The International Society for Optical Engineering | Year: 2014

This paper describes the Electrical Ground Support Equipment (EGSE) of the Dust characterization, Risk assessment, and Environment Analyser on the Martian Surface (DREAMS) scientific instrument, an autonomous surface payload package to be accommodated on the Entry, Descendent and landing Module (EDM) of the ExoMars 2016 European Space Agency (ESA) mission. DREAMS will perform several kinds of measurements, such as the solar irradiance with different optical detectors in the UVA band (315-400nm), NIR band (700-1100nm) and in "total luminosity" (200 -1100 nm). It will also measure environmental parameters such as the intensity of the electric field, temperature, pressure, humidity, speed and direction of the wind. The EGSE is built to control the instrument and manage the data acquisition before the integration of DREAMS within the Entry, Descendent and landing Module (EDM) and then to retrieve data from the EDM Central Checkout System (CCS), after the integration. Finally it will support also the data management during mission operations. The EGSE is based on commercial off-the-shelf components and runs custom software. It provides power supply and simulates the spacecraft, allowing the exchange of commands and telemetry according to the protocol defined by the spacecraft prime contractor. This paper describes the architecture of the system, as well as its functionalities to test the DREAMS instrument during all development activities before the ExoMars 2016 launch. © 2014 SPIE. Source


Lazzarin M.,CISAS | Biolo M.,CISAS | Bettella A.,CISAS | Manente M.,CISAS | And 2 more authors.
Aerospace Science and Technology | Year: 2014

This paper presents a research work estimating the impact of propellant sloshing on the pointing-stability of the EUCLID satellite, for a pre-design phase of the project. The analysis is carried out by means of a simplified lumped parameter model describing the fluid system. This model allows the identification of forces and angular moments due to liquid movement under different acceleration conditions, and for different fill levels of the reservoir. The lumped model is calibrated by means of CFD simulations to determine the correct values to be attributed to the different coefficients. For this work, two tank fill ratios have been considered: 22 and 50%, with an elastomeric and deformable bladder. The results of the lumped models are compared with the CFD output obtained using the same acceleration profile, and corresponding to the same fill level. The study shows that using CFD to calibrate the lumped parameter model is a promising technique, which can be applied at a preliminary design stage, to reduce development costs and time. This work is intended as the prosecution of the first study about sloshing by the same authors, which was aimed at representing bladdered tanks using computational fluid dynamics without recurring to fluid-structure interaction techniques. Here, a new method for the calibration of the traditional sloshing lumped model, based on computational fluid dynamics instead of real experiments, is proposed and applied to a specific fluid system. This procedure can result in a consistent reduction of the experiments costs. © 2014 Elsevier Masson SAS. All rights reserved. Source

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