|
Disertaciones |
|
1
|
-
WILLIAM HUMBERTO ÚSUGA GIRALDO
-
Mask technique for detecting space debris with ground telescope images acquired in static mode
-
Líder : JOSE DIAS DO NASCIMENTO JUNIOR
-
MIEMBROS DE LA BANCA :
-
JOSE DIAS DO NASCIMENTO JUNIOR
-
JEFFERSON SOARES DA COSTA
-
LEANDRO DE ALMEIDA
-
Data: 31-ene-2022
-
-
Resumen Espectáculo
-
Orbital debris of approximately 10 cm in size can be measured with ground-based telescopes. This debris threatens the functioning of satellites and has an impact on the economy and the global security of space activities. In the GEO orbit, where most of the economically active satellites are located, exists approximately 842 cataloged debris. On the other side, orbiting LEO exists approximately 13485 debris cataloged. In this context, the ESA studies show that hundreds of millions of small objects over 1 mm are currently in the two orbits GEO and LEO above the Earth and have not yet been cataloged. In this study, we created a computational procedure to detect space debris in GEO orbit based on images obtained from ground-based telescopes on the static mode. In this mode, the field sky stars appear as lines in the CCD images and the garbage in the form of dots. CCD images of 2992 x 2092 pixels (high resolution) and with 5 degrees of field of view (FOV) and with 7 seconds of exposure used in this work were obtained with the PanEOS telescope (Panoramic Electro-Optical System), 750 mm aperture, and installed at the Picos dos Dias observatory of the National Astrophysics Laboratory (LNA). For this research, we adapted the Photoutils package written in Python to build a mask and separate stars from candidates for space debris. Our methodology consisted of first smoothing the images using a Gaussian Kernel filter, then each element was categorized into two categories, and finally, the stars were erased resulting only in space debris candidates. We tested combinations of flow to establish the detection limit and used the different points spread function (PSF) to determine the limit of the elongation of objects. Our methodology works with a single image at a time in a fast and efficient way. This allows us to detect objects with different PSF and therefore requires low hardware capability. Our results in this validation phase identified 100% of the artificial training debris. In the real images of the PanEOS telescope, we detected a few real debris consistent with the expected size. In the next steps, we must estimate the size of the object and characterize its orbit.
|
|
2
|
-
JULIANA JENIFFER FERNANDES DE SOUZA RÊGO
-
Ballistic armor design of the as-350 helicopter from numerical-experimental analyses.
-
Líder : DINO LINCOLN FIGUEIROA SANTOS
-
MIEMBROS DE LA BANCA :
-
DINO LINCOLN FIGUEIROA SANTOS
-
JOSE DANIEL DINIZ MELO
-
JOSÉ VIRGÍLIO GUEDES DE AVELLAR
-
VIVIANE MUNIZ FONSECA
-
Data: 14-feb-2022
-
-
Resumen Espectáculo
-
Helicopters used in public safety operations go through several risk situations involving ballistic projectiles, one of the safest solutions is armor, offering maximum protection combined with technology.
The present work aims to project an armoring system for the AS-350 helicopter, using as material the polymer matrix composite reinforced with para-aramid fiber and glass fiber. Considering the airworthiness requirements and the restrictions determined by the manufacturer, an analytical method was used to study the effects of armor on the weight and balance of the aircraft. The project used the Aerospace Design Methodology in conducting the work.
To verify the efficiency of the ballistic composite, the experimental tests were carried out in an open outdoor environment where the composite was exposed to the impact of projectiles with a caliber of 5.56x45 mm. The performance of the material was analyzed by the results obtained in the tests and, this provided the determination of the protection reliability of the ballistic system.
The armor design for the AS-350 proved to be safe to be installed on aircraft of this model, as a level III ballistic protection tool, without impairing its mobility.
|
|
3
|
-
ELDER SAMUEL TAVEIRA DA SILVA
-
PRELIMINARY DESIGN OF A NANOSATELLITE LAUNCH VEHICLE USING SCRAMJET TECHNOLOGY
-
Líder : DOUGLAS DO NASCIMENTO SILVA
-
MIEMBROS DE LA BANCA :
-
DOUGLAS DO NASCIMENTO SILVA
-
JOSE HENRIQUE FERNANDEZ
-
PAULO GILBERTO DE PAULA TORO
-
JOÃO FELIPE DE ARAÚJO MARTOS
-
Data: 17-feb-2022
-
-
Resumen Espectáculo
-
This Master's Dissertation presents a preliminary design of an aerospace vehicle, using hypersonic airbreathing propulsion based on supersonic combustion (scramjet technology), for atmospheric flight at 20 km altitude, at hypersonic speed, corresponding to Mach number 5.79. Scramjet is an aeronautical engine without moving parts, where the aerospace vehicle integrated with scramjet technology (propulsion system) must be coupled to a rocket engine. The current means of access to space is limited by the chemical propulsion system (solid and / or liquid fuel) carried onboard rockets. The technology of supersonic combustion (scramjet) is being studied as an airbreathing propulsion system, to be used in the dense layers of the Earth's atmosphere, to access space. A demonstrator is being designed to be coupled to the Sonda III rocket engine, to operate as a second stage, starting the operation at 20 km altitude. The theory of oblique shock waves, the theory of heat addition in one-dimensional flow (Rayleigh's theory) and the theory of expansion waves (by Prandtl-Meyer) coupled to the area ratio are applied in the design of the compression sections, of combustion and expansion, respectively, of the scramjet demonstrator with internal admission configuration. Steady state, one-dimensional flow and air under calorically perfect gas conditions will be considered. Thermodynamic properties (pressure, temperature, density, speed of sound) and flow velocity (Mach number) will be presented along the streamline from the leading edge to the trailing edge of the demonstrator, considering flow without and with boundary layer effects, for the conditions of no fuel burning (power-off) and fuel burning (power-on). Finally, the conceptual design and a brief approach to systems engineering in the development of a nanosatellite launch vehicle are presented.
|
|
4
|
-
MARCOS VINICIUS SABINO PEREIRA
-
Preliminary design of a scramjet to insert cubesat into orbit
-
Líder : SANDI ITAMAR SCHAFER DE SOUZA
-
MIEMBROS DE LA BANCA :
-
DOUGLAS DO NASCIMENTO SILVA
-
HEIDI KORZENOWSKI
-
PAULO GILBERTO DE PAULA TORO
-
SANDI ITAMAR SCHAFER DE SOUZA
-
Data: 19-feb-2022
-
-
Resumen Espectáculo
-
In order to access the space through the application of hypersonic airbreathing propulsion technology, this work proposes the development of a scramjet (supersonic combustion ramjet). The aerospace vehicle proposed in this work will have three stages, two stages of rocket engines with solid propulsion and a stage composed by a scramjet with four combustion chambers. The scramjet of this vehicle will operate in vertical flight in the Earth’s atmosphere, from 20 km to 60 km of altitude with hypersonic speed corresponding to approximately Mach number 5.8. Bearing in mind that the scramjet has no moving parts and needs a system that accelerates it, up to supersonic combustion conditions, it will be necessary to use the accelerator vehicle that is responsible for propelling the scramjet to the ideal operating conditions (Mach number, position, dynamic pressure). This aerospace vehicle will have the utility of accessing space and conducting drilling experiments, injecting CubeSat into orbit and training the specialized labor responsible for aerospace operations. For the preliminary development of this work, it is necessary to use the theories referring to the formation of shock waves and expansion waves, in addition to the theories related to the addition of heat and the formation of a boundary layer in flow with hypersonic velocity. Therefore, for this development the analytical theoretical methodology was applied and then with the results obtained it was possible to carry out, in the near future, the preliminary mechanical design that determines the necessary basic measures, in addition to the possible materials to be used in the vehicle. The preliminary results of this work indicate that the scramjet will be able to generate thrust and that when considering the existence of the boundary layer, a change in the geometry of the vehicle's inlet is necessary, so that it is possible to maintain the formation of shock-on-lip and shock-on -corner in the scramjet structure.
|
|
5
|
-
ARTHUR BANDEIRA LUZ DE LIMA
-
A study about the influence of the solar cycles in the atmospheric conditions over the Curitiba Flight Information Region
-
Líder : JOSE HENRIQUE FERNANDEZ
-
MIEMBROS DE LA BANCA :
-
DINO LINCOLN FIGUEIROA SANTOS
-
FILIPE EMANUEL VIEIRA TAVEIROS
-
JOSE HENRIQUE FERNANDEZ
-
Data: 21-feb-2022
-
-
Resumen Espectáculo
-
Atmospheric conditions are mostly driven by the Sun, which follows a cycle of activity whose duration is about 11 years. Since this cycle has been found out, researchers has brought up the hypothesis that it may have some influence at the lower atmosphere, taking as proxies the Carbon-14 and Berilium-10 concentration in tree rings and ice cores. Beside that, some manuscripts have shown that, during the Maunder Minimum, where the Sun were at minimum of activity, some regions over the globe experienced a tiny "Ice Age". Initially, it was believed that this influence was related to the Total Solar Irradiation variation during a cycle. Although, further studies have shown that such variations were a rather small to produce these variations on the lower atmosphere. So, they have created the hypothesis that these influence was related to the solar cycle on the Galactic Cosmic Rays (GCR) flux through the heliosphere. GCR work as a ionizing agent, favoring the aerosol synthesis, which acts as Condensation Nuclei, which favors clouds formation. So, the objective of the research was to find a correlation between the solar cycles and meteorological conditions in the region where the cities of Rio de Janeiro e São Paulo are located. In this region, a huge flux of aircraft is observed.
|
|
6
|
-
BENJAMIM MONTEIRO DA SILVA NETO
-
DEVELOPMENT A MOBILE PLATAFORM APP FOR THE RISK MANAGEMENT OF NANOSATELLITE PROJECTS
-
Líder : GIULIANI PAULINELI GARBI
-
MIEMBROS DE LA BANCA :
-
FRANCISCO JOSE TARGINO VIDAL
-
GIULIANI PAULINELI GARBI
-
MARCOS AURELIO FERREIRA DOS SANTOS
-
Data: 22-feb-2022
-
-
Resumen Espectáculo
-
Within Systems Engineering, risk management processes are mandatory requirements in satellite missions, being used on a large scale for large satellites. However, traditional approaches need adaptations to be applied, in a viable way, to missions with small satellites due to the costs and deadlines involved. This work aims to design, implement, and disseminate a risk management methodology adapted to small satellites. To this end, it is proposed to create an application to perform this management, using the necessary adaptations for application to this type of mission. The bibliographic research methodology was used to characterize small satellites, mostly the CubeSat platform, and the description of methods and risk management tools used worldwide, as well as their applications to small satellite projects. For the design of the application, the Java language will be used. The application’s functionalities were chosen to provide agility, ease, and integration with the risk management processes. The work is divided into five chapters. The first one consists of an introduction. The second presents a historical reinterpretation of small satellites, definitions of them, and their importance. The third chapter deals with systems engineering and risk management. The fourth chapter presents examples of risk management adapted for nanosatellites. And the fifth chapter presents the proposed solution to the problem raised.
|
|
7
|
-
RAFAEL ALVES FREIRE
-
Stellar Rotation Period Versus Energy Variation of Flares in TESS Stars of Spectral Types K and M
-
Líder : JOSE HENRIQUE FERNANDEZ
-
MIEMBROS DE LA BANCA :
-
JOSE HENRIQUE FERNANDEZ
-
DOUGLAS DO NASCIMENTO SILVA
-
JOSE RENAN DE MEDEIROS
-
ANTONIO CARLOS DA SILVA MIRANDA
-
Data: 24-feb-2022
-
-
Resumen Espectáculo
-
Under the development of new technologies, the Aerospace Engineering is increasingly improving its equipments in order to assist exploration that goes beyond our Heliopause. As an example of this we can cite the launch of the space artfact Transiting Exoplanet Survey Satellite (TESS) that has been contributing photometric data to Space Sciences, like Astrophysics, with the aim of study various physical phenomena. As an exemple, the magnetic activity of stars can be fundamental in forming the atmosphere of exoplanets and impact your habitability as well as, it can trigger life in the orbit of type K and M stars, which are considered to be cold and they are the most numerous in the main sequence phase in the Hertzsprung-Russell diagram. Based on these investigations and through statistical analysis of the behavior of stellar flares in relation to their classi cations, rotational periods and spectral subtype, this dissertation presents a study on the variation of energie of stellar flares as a function of their rotational period in a sample of 679 TESS stars of spectral type K and M. None of the stars in this sample showed a correlation between the energy of their surface stellar eruptions as a function of their rotational period. Finally we present four scenarios involving the stars and their stellar eruptions and theirs that can explain our results.
|
|
8
|
-
THIAGO FONSECA MESSIAS
-
Test of a UHF receiver to collect satellite sensor data
-
Líder : JOSÉ MARCELO LIMA DUARTE
-
MIEMBROS DE LA BANCA :
-
FRANCISCO DE ASSIS BRITO FILHO
-
FRANCISCO JOSE TARGINO VIDAL
-
JOSÉ MARCELO LIMA DUARTE
-
Data: 25-feb-2022
-
-
Resumen Espectáculo
-
This master’s thesis presents a test plan, the automation system for carrying out the experiments and the results obtained from the Environmental Data Collector (EDC), UHF receiver for collecting data from satellite sensors. The parameters tested were: bandwidth, linearity, spurious, noise figure and performance of the decoding the received signals. The EDC will act in the space segment of the Brazilian Environmental Data Collection System (SBCDA), a forwarding system for satellite message. For over twenty years, the SBCDA has provided data for various surveys. sas, however, the SBDCA needs an update to its space segment. The Institute National Space Research Institute is developing a constellation of nanosatellites from the CubeSat standard to replace the current SBCDA satellites. The EDC will be the payload of the new SBCDA nanosatellites. To validate the EDC, a test plan was prepared which aims to assess whether the prototype built is in accordance with the desired specifications. To carry out the tests, a bench equipped with a computer was built, equipped with testing software, a signal generator, a voltage source and a Arduino. A spectral analysis, from the digitized signal, was used for the tests. of the RF-Front-End and the Frame Error Rate calculation was used to validate the capacity of the EDC to decode incoming messages. The EDC prototype was approved with based on the results obtained, however, some corrections were suggested.
|
|