Com a Revolução Cubana a Guerra Fria se torna mais presente no continente americano. O governo dos Estados Unidos da América começa a desenvolver ações para combater o governo revolucionário que assume o poder naquele país. Essas ações são baseadas no emprego da força militar e em soluções diplomáticas. Nesse mesmo período, João Goulart se torna presidente do Brasil. Ele continua a Política Externa Independente do governo Jânio Quadros. E o governo brasileiro acaba se envolvendo na questão de Cuba. Esta tese procura investigar a participação do governo de João Goulart na Crise dos Mísseis (1962) e compreender o que esse episódio representa para a Política Externa Independente. Nossos objetivos são demonstrar como o Brasil percebe a evolução da questão de Cuba; perceber como o país se posicionou na Organização dos Estados Americanos (OEA) e quais foram as repercussões decorrentes; procurar entender qual a razão do envio do general Albino Silva à Cuba; compreender a posição brasileira na Organização das Nações Unidas (ONU) através do projeto de desnuclearização da América Latina; verificar como a sociedade brasileira se manifestou a respeito desse episódio; e, por fim, analisar se a Crise dos Mísseis modifica as relações entre os governos de Goulart e Kennedy. / With the Cuban Revolution to Cold War becomes more present in the Americas. The government of the United States of America begins to develop actions to combat the revolutionary government that assumes power in that country. These actions are based on the use of military force and diplomatic solutions. In the same period, becomes president of Brazil João Goulart. He continues the Política Externa Independente of Quadros government. And the brazilian government gets involved in the issue of Cuba. This thesis investigates the involvement of the government of João Goulart in Missile Crisis (1962) and understand what this episode is for the Política Externa Independente. Our objectives are to demonstrate how Brazil sees the evolution of the issue of Cuba; see how the country stood at the Organization of American States (OAS) and what were this repercussions; seek to understand the reason of sending general Albino Silva the Cuba; understand the brazilian position at the United Nations (UN) through the project of denuclearization of Latin America; check how brazilian society manifested related to this episode; finally, analyze the Missile Crisis produced some effect in relations between the governments of Goulart and John Kennedy; analyze if the Missile Crisis modifies the relations between the government of Goulart and Kennedy.

No description available.

Aerocapture offers a near propellantless and quick method of orbit insertion at atmosphere bearing planetary destinations. Compared to conventional propulsive insertion, the primary advantage of using aerocapture is the savings in propellant mass which could be used to accommodate more useful payload. To protect the spacecraft from the aerodynamic heating during the maneuver, the spacecraft must be enclosed in a protective aeroshell or deployable drag device which also provides aerodynamic control authority to target the desired conditions at atmospheric exit. For inner planets such as Mars and Venus, aerocapture offers a very attractive option for inserting small satellites or constellations into very low circular orbits such as those used for imaging or radar observations. The large amount of propellant required for orbit insertion at outer planets such as Uranus and Neptune severely limits the useful payload mass that can delivered to orbit as well as the achievable flight time. For outer planet missions, aerocapture opens up an entirely new class of short time of flight trajectories which are infeasible with propulsive insertion. A systems framework for rapid conceptual design of aerocapture missions considering the interdependencies between various elements such as interplanetary trajectory and vehicle control performance for aerocapture is presented. The framework provides a step-by-step procedure to formulate an aerocapture mission starting from a set of mission objectives. At the core of the framework is the ``aerocapture feasibility chart", a graphical method to visualize the various constraints arising from control authority requirement, peak deceleration, stagnation-point peak heat rate, and total heat load as a function of vehicle aerodynamic performance and interplanetary arrival conditions. Aerocapture feasibility charts have been compiled for all atmosphere-bearing Solar System destinations for both lift and drag modulation control techniques. The framework is illustrated by its application to conceptual design of a Venus small satellite mission and a Flagship-class Neptune mission using heritage blunt-body aeroshells. The framework is implemented in the Aerocapture Mission Analysis Tool (AMAT), a free and open-source Python package, to enable scientists and mission designers perform rapid conceptual design of aerocapture missions. AMAT can also be used for rapid Entry, Descent, and Landing (EDL) studies for atmospheric probes and landers at any atmosphere-bearing destination.

The aim of this work is to test the ability of three selected theoretical approaches to explain the response of the Czech Republic to the American offer to build the ABM radar device on the Czech soil. These theories are: neorealism, utilitarian liberalism and constructivism. Each of these approaches looks at the social reality from a different perspective which allows us to view the issue in its complexity and diversity. Each theory also uses a different set of independent variables to explain the behavior of the Czech government in this case (these variables are: autonomy and influence for neorealism; domestic interests for liberalism and international and domestic norms for constructivism). Thanks to this variety of variables we are enabled to critically evaluate which key factors played the crucial role in the Czech decision-making process in this particular issue and possibly also to point out some assumed regularities which might play an important role in forming of the Czech security policy as such. The main task of the first chapter is to provide some broader historical and political context of the case. Next three chapters are then dedicated to testing of the theories by comparing their deductively phrased hypothesis with the value of dependent variable, which for our work is represented...

Master thesis analyzes strategic behavior of the PRC in the region of the Northeast Asia in direct relationship with regional missile defense. The aim is to analyze motives of China`s regional strategic behavior with respect to the specific technological element (= Theatre Missile Defense) on the basis of predetermined analytical levels: realistic, liberal and constructivist. But there are great differences in technological configuration of individual missile defense systems or in the configuration of the relationship of regional actors with the PRC. Thus the thesis will comprise of case studies analyzing the complex relationship of the PRC and regional actors (that are creating regional missile defense). The creation of regional missile defense can endanger China`s vital strategic interests (in the region of Northeast Asia) under specific conditions. But the regional strategic behaviour of the PRC is moderate. The aim is to explain, why the PRC does not change its regional strategic behavior in direct connection with emerging theater missile defence.

The diploma thesis "Strategic Defense Initiative" deals with the issue of the Strategic initiative on the basis of historical-political analysis. The SDI was a crucial topic during the 80s, which had political impacts on the development of the international events and the Cold war in general. This work presents brief history of the United States ABM systems and introduced historical context. Furthermore, the author analyzes possible reasons for the SDI announcement and reexamines Reagan's speech from March 1983. Persons and interest groups who were promoting strategic defense are also included in this analysis. Problems connected to the SDI and its brief description are also mentioned. The following chapter deals with Soviet reaction to the SDI. The seventh chapter dicusses the European reaction to the SDI. The topic is analyzed on the example of United Kingdom. Next chapter deals with the Anti Ballistic Missile treaty and its interpretations from the SDI prespective. Last chapter discusses US - Soviet summits which took place in the 80s with emphasis on the SDI.

Modern-day terrorist attacks present a considerable danger for commercial aircrafts. This thesis analyzes potential methods of such attacks with a critical analysis of the most dangerous type: an attack from the outside of the aircraft via a fragmentation missile warhead. Such missiles cause damage to the airframe of the aircraft through fragments created by the explosion. In this thesis, analytical geometry is used to determine the area of the aircraft affected by the fragmentation. The aircraft’s geometry and the fragments’ dispersion are calculated by analytical functions, and the effect of the damage is analyzed. A shooting experiment was also carried out, in which fragments were shot at a reinforced skin panel that was manufactured according to the real design of commercial aircraft. The results of the experiment revealed that only directly hit sections of the structure are damaged. Data obtained by the experiment was then used for the creation and improvement of the model used in the simulation by means of the finite element method. This model is used for the numerical calculation of the damage sustained. Further included in the thesis is an analysis of the change in the load-bearing capacity after such an attack. The relationship between the size of the damage and its effect on the load-bearing capacity of the component as well as the entire structure is defined. First, the effect of component damage is analyzed via the FMEA/FMECA methods. This analysis is then extended using fuzzy logic. Fuzzy logic analysis is based on the determination of the size of the damaged component area and the component’s importance on the structure’s carry loads. Application of the defined approach is described for several parts of an aircraft’s life cycle, including development, operation after the terrorist attack, and assessment of causes after a crash caused by a fragmentation missile warhead.

No description available.

No description available.

<p>As the small satellite market has grown from a niche of the space economy to a full commercial force,  microthrusters remain an area of significant growth in the space industry as new technologies mature. The \textit{Film-Evaporation Microelectricalmechanical Tunable Array} (FEMTA) is one such device. FEMTA is \textit{microelectricalmechanical system} (MEMS) device that harnesses the microcapillary action of water and vacuum boiling to generate thrust. The water propellant is not chemically altered at all by the process; it is simply evaporated. This technology has been tested in relevant laboratory environments, and a suborbital flight opportunity in 2023 as a payload on a Blue Origin New Shepard rocket  will grant FEMTA a demonstration in a space environment. The flight will provide 150 seconds of weightlessness at the zenith of the suborbital flight path before the booster returns to land. During weightlessness, the experiment will be exposed to the ambient environment allowing for a full capability test of the thruster. The experiment is meant to demonstrate the propellant management system for FEMTA in 0G and measure the thrust produced by a FEMTA thruster.</p> <p><br></p> <p>The propellant management system portion of the experiment consists of an oversized version of the subsystem intended for use in the thruster. The propellant management system uses a hydrofluoroether to inflate a diaphragm to ensure constant wetting of the propellant tank exit and nozzle inlet. The experiment will take tank pressure data and flow sensor data to understand the system's behavior. The system is duplicated for redundancy and to double the possible data. This system requires further testing before being prepared for launch, vibrational testing, thermal testing, and vacuum testing. </p> <p><br></p> <p>The 0G thrust experiment and plume analysis portion of the experiment consists of numerical modeling and a novel thrust measurement approach. \textit{Direct Simulation Monte Carlo} (DSMC) is being applied to understand the pressure, density, and temperature distributions of the plume of water vapor produced by the FEMTA thruster. The FEMTA nozzle environment is challenging to simulate with computational fluid dynamics  or DSMC due to chaotic transient effects and because both the continuum and molecular regimes must be considered. The current analysis consisted of a two-dimensional model and investigated the effect of meniscus location and contact angle on thrust generated.</p> <p><br></p> <p>It is not possible to use traditional thrust measurement devices (sensitive torsional thrust stands or microsensors intended for use on small satellites) for microthrusters on a rocket booster. Two  novel approaches for performing thrust measurement in the range of 100 microNewtons have been investigated. The first approach ionizes the FEMTA thruster plume and analyzes the plasma by optical emission spectroscopy. The theory states that the relative intensity of a given wavelength observed correlates to the density of the species in the plasma. The density of water would be directly correlated to the thrust generated by FEMTA during the experiment, as more water is evaporated as thrust is increased. This method is no longer being considered for the suborbital experiment but did yield promising results. </p> <p><br></p> <p>The second approach employs a d'Arsonval meter, a photo-interrupt, and an Arduino controller. The d'Arsonval meter consists of a stationary permanent magnet with a moving coil and a pointer. Increasing the voltage in the coil causes a torque on the system due to the magnetic field induced by the permanent magnet. This torque causes a deflection of the pointer that is proportional to the voltage applied. The flag of the sensor will be placed in the path of the gas jet from the thruster. The force caused by the jet pressure will move the flag. An Arduino controller will vary the voltage to hold the flag in place. As the mass flow rate increases, the reaction force required to hold the flag in place will increase. This sensor can be calibrated using an analog cold gas system that passes various gases (air nitrogen, argon, etc.) through an orifice nozzle at mass flow rates that are set by a mass flow rate controller. DSMC analysis has been performed to understand the flow field and flow properties and how they directly relate to the force experienced by the flag sensor. </p> <p>An undergraduate course has supported parts of the work described in this dissertation. This course has applied the Vertically Integrated Projects approach to project-based learning. This method and its results were analyzed and lessons learned as well as a blueprint for future application of this method to other small satellite projects are discussed.</p>