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CoPt-based thin PLD systems for high density magnetic recording. Conventional and tilted perpendicular recording
No full textRoberto Paolesse, Lucio D'Ilario, Maria Letizia Terranov
Ruolo dell'IGF1 nello sviluppo e progressione della colestasi sperimentale ed umana
No full textDomenico Alvaro, Adelaide Continenza, Giuseppe Ricciard
" Molecular mechanism of the Ca2+-dependent activation of sorcin (soluble resistance-related calcium binding protein. A study with site-specific mutants."
No full textFiliberto, Cimino Maria Rosa, Ciriola Massimo Castagnol
La fibrogenesi epatica: markers precoci e meccanismi regolatori
No full textDomenico Alvaro, Adelaide Continenza, Giuseppe Ricciard
La Piazza da "Nodo Superficiale" a "Nodo Integrale" Modelli di Analisi e Rappresentazione
No full textEmma Mandelli, Giuseppe Pagnano, Livio Sacch
Percezione e geometria. L'informatizzazione della geometria descrittiva per la creazione di nuovi modelli finalizzati alla percezione attiva degli spazi multimediali.
No full textEmma Mandelli, Giuseppe Pagnano, Livio Sacch
DESIGN, SYNTHESIS AND BIOLOGICAL VALIDATION OF EPIGENETIC MODULATORS OF HISTONE/PROTEIN DEACETYLATION AND METHYLATION.
No full textGino Lucente, Paolo Arese, Mauro Piacentin
PROGETTO PER L’ASSEMBLAGGIO DI UNA BASE LUNARE MOBILE MODULARE – ESPANDIBILE
No full textThis work speaks about the possibility to build a Lunar Base Habitat.
Some of the technologies proposed are not completely yet available they are in
developing state.
Many aspects have been covered, from the type of launcher which mainly dictates the
masses, dimensions constraints; to the use of inflatable structures which could be
adopted to increase the habitat volume while contemporary decreasing the total
habitat mass.
Others important aspects analyzed are a new approach to the Micro Meteoroids
shielding system and a new method for the Galactic Cosmic Radiation protection
system.
This work does not cover problems like Air, Water and Food on the Moon.
LANDER (required to transfer the Moon Base Modules form lunar orbit to lunar
surface), are considered and analyzed, only from mass and engine type points of
view, the design of LANDER it is not object of this work.Chapter 1
Describe many Moon Base projects and many of the ideas freely available on the
Internet. It also speaks about the problems concerning Sun Light availability,
potential Water availability and consequently about the best possible area to build a Lunar Base. At the end of the chapter one the Moon Quakes phenomena are shown too. Chapter 2
The basic ideas of the Moon Habitat Modules, in this thesis developed, are presented
In this chapter. The main constraints which have been adopted in order to design the
Moon Habitat Modules are also shwon.
Problems like Mass, Volume, Moon Base Safety during landing of the resting
Modules, Module’s Inflatable Connection Structures, Solar Array, Mobile Equipment
of each Module, Potential Space Vehicle requred to transport these Moon Modules
from Earth to the Moon, are analyzed.
The main focus in this chapter is to describe the so called LEMMB (LunarExpandableMobileModularBase)
and, all the main phases required to connect
several LEMMBs to each other in order to build a large Moon Habitat.
This chapter reports the main characteristics of LEMMB and tray to explain how the dimensions are compliant to those of Ariane 5 and Soyuz Space Vehicle usable
internal firing volume. Chapter 3
This chapter describes the LEMMB structures and materials, the inflatable structures
with relative supports, a new approach to the MM/OD (Micro Meteoroid / Orbital
Debris) protections system, and contemporary speaks about a passive shielding
system against Galactic Cosmic Rays. This passive shielding could be made by
polyethylene which similar to the liquid Hydrogen presents a high ionizing radiation
absorption behavior.
The idea of new approach for the MM/OD (Micro Meteoroid / Orbital Debris)
protections system is an applications of recent studies made in the Department of
Mechanical and Aerospace Engineering, University of California at San Diego, La
Jolla, California.
This publication reports the first experimental observation of impulse confinement and the disintegration of shock and solitary waves in onedimensional
strongly nonlinear composite granular materials. In order understand the phenomena; I have made some assumptions about momentum transfer which are not completely verified in the strongly non linear real system. This assumption simplifies the mathematical model and can help us to understand one of the most processes which contribute to the shock disintegration effect.
The most part of the considerations about LEMMB are discussed here taking into
account LEMMB mass constraint which mainly depends on cost of launch and available launcher.
Almost all the pictures have been created by using Autocad. Chapter 4
This chapter is focused on a possible European Launcher to be used in order to bring up the LEMMB modules from Earth onto Low Lunar Orbit.
Since the total mass of LEMMB plus LANDER should be about 23 tons, the today’s
version of Ariane 5 can not be used, in fact it can transport maximum a mass of 3.2
tons on a typical lunar orbit.
Recent studies on a new generation of the Ariane launcher called “Ariane Heavy
Lift”, show the possibility to bring up, on Low Lunar Orbit, a payload mass up to
about 40 tons.
Starting from the Ariane 5 usable internal firing volume, it has been defined the
dimensions of the LEMMB modules. These dimensions are compliant with Soyuz
internal firing volume too.
In order to have an idea of the velocity impulse required to complete a lunar mission,
some computations have been performed using Hohmann transfer as a typical transfer
method. The results have been compared to those obtained using other typical
literature methods like Patched Conic approach. The obtained final values are similar
and are also close to the values on literature available.
At the end of chapter some considerations on LANDER engine type and on the
LANDER propellant mass have been done.
These considerations starts taking into account Tsiolkovsky equations, storable type
of propellant used and, LEMMB plus LANEDR structures and payload total mass. All off these considerations have the purpose to find the propellant mass of LANDER
and consequently the total mass of LEMMB plus LANDER. This total mass of about
23 tons is the mass to be considered as a useful payload in order to choose the best
Launcher Space Vehicle. Chapter 5
This chapter tries to cover the electrical power generation problems. Solar energy
could be used by adopting Photovoltaic Solar Arrays.
In order to understand which type of solar array could be used, an extensive analysis
of the today’s solar array market has been done.
This analysis has taken into account that in the space the most important aspect, are
high efficiency, light weight and space environment resistance. Costs of solar cells
are not the main driver in space applications.
Thin film amorphous silicon solar cell could be used because they are very tin but
their efficiency is lower than single crystalline solar cell. Since the efficiency is a very important aspect in space then, at the end, the final choice is fallen on solar
arrays similar to those currently used on ISS (International Space Station). The
present specific power (P/M, power per unit mass) of singlecrystal silicon solar
panels on the International Space Station (ISS) is < 0.1 kW/kg .
Note that crystallineSi cells are ~ 300 μm thick, whereas thin films cells under
development for Earth and space applications are ~ 1 μm.
Moreover, ultralight support structures made of inflatablerigidizable structures are
possible for space PV. Thinfilm PV on “gossamer structures” could raise P/M to the
110 kW/kg range.
Inflatable solar array has been considered too, but because of the LEMMB shape, the
best solution for a today’s solar array application seems a folded and accordion
deployable systems like used on ISS where. In place of the ISS Solar Array Beta
Gimbal Assembly ( mechanism used to develop the solar array), the LEMMB
connections Inflatable structures has been adopted. Chapter 6
This chapter covers the most important problems due to space radiations like GCR
(Galactic Cosmic Rays) and SPE (Solar Particle Event).
Radiations are very dangerous for astronaut’s health. Electronics circuit could be seriously damaged due to this Space Radiations too.
In the first part of chapter, all of the main hazard radiations types are analyzed.
In the second part some shielding method are presented. The methods currently
available on literature are mainly passive or static active.
Passive shield (i.e Conventional method) like Lunar Lava Tube passive shielding
system.
Active Shielding as Electrostatic shield – electric field only (timeindependent)
; or Magnetic shield – magnetic field only (timeindependent) or Both Electric and
Magnetic fields (timedependent,)
developed in this thesis.
This last new approach has the advantage of the Electromagnetic wave propagation
effect. A propagating Electromagnetic wave can be emitted by an antenna which is a
very well proven technology.
By means of the Circular Polarized EM wave it seems possible to deflect a charged
particle coming as an example from the Sun. The idea is well explained in this
chapter.
In order to find the deflection particle trajectory both, Lorentz equations and
Electromagnetic Wave Propagation equations have been combined together. Since
their integration is not very easy then, two integration method have been developed;
one in a closed form and another one in numerical form.
Result from both method are close to each other.
In numerical Integration method also the Errors problems have been analyzed. Chapter 7
In order to prove the active time dependent charged particles deflection method
studied and proposed in chapter 6, an experiment has been done. The experiment consists in deflecting the electrons beam produced within a CRT (Cathode Ray Tube), by using an Electromagnetic wave circular polarized.
For this experiment all the instrumentations used have been kindly made available by
TILAB (Telecom Italia LAB).
The source of charged particles (electrons) is an Oscilloscope CRT.
The experiment results show some effects which could have been produced by the
deflection mechanism explained before. The deflection amplitude seems also close to
what expected form theory point of view.
Nevertheless, some doubts remain because of the potential errors due to
Electromagnetic Compatibility problems.
This aspect is worthy of more studies. Appendix
The thesis appendix reports the Matlab and C code, used in order to find the charged
particle deflection trajectory, by computing the integration of the second order
equations
The structure of the NO-sensing domain of the transcription factor DNR from Pseudomonas aeruginosa
No full textMassimo Castagnola, Filiberto Cimino, Maria Rosa Ciriol