This thesis focuses on the use of magnetic levitation technology as a means to provide launch capability to future space bound vehicles. Building on past work and after an extensive literature review, we aim to show how magnetic levitation and propulsion can be an economically and socially justifiable means to launch cargo and passengers for the purpose of reconnaissance, space tourism, and deep space exploration. Based on the validity of the technology, we look at the economic and political viability of establishing a magnetic levitation and propulsion launch system and compare it with current launch systems. With the recession caused due to the market crash in 2008-09 and the national space budget constrictions that followed, it is easy to establish that any project of this scale would not only require international collaboration and cooperation, but also an international framework developed from the ground up to engage private enterprise and promote public-private partnerships. As the United States of America accounts for over 75% of global space spending, we focus on the impact of its internal policy and legislation such as the International Traffic in Arms Regulations and the United States munitions list that have a direct impact on collaborative and cooperative efforts made by public and private entities within the United States. The thesis goes on to describe how a new global space policy for civil and commercial projects could potentially pave the way for new avenues of collaboration and inclusion of actors who for the time being are unable to participate in the space arena either due to lack of available funds or technology inputs. This thesis and the publications based upon it, aims to define a new era in international cooperation, with a magnetic levitation and propulsion project being a technological test -bed that would help validate the cooperation scenario.

This thesis proposes the design of a space exploration vessel capable of sustaining a community of 2000 inhabitants that will leave Earth and never return. The unique mission criteria will allow for the in depth study of fundamental architectural issues such as confinement, permanence, habitability, and wellbeing. The vessel, named Horizon, will address the social, cultural, and environmental systems necessary for maintaining a platform for an evolving community. Emphasis throughout the thesis will be placed on the human condition and social systems rather than technical details and specifications of the ship’s construction. A human settlement travelling through the void of space and severing its ties with Earth creates an intense design challenge. How can architecture create a stimulating and humane environment without a traditional sense of site or any of the Earthly conditions that can influence memory, stimulate growth, and sustain culture? The final presentation of the thesis will take the form of an illustrated narrative. This form of representation will allow for the blending of fact and fiction, producing a narrative in the tradition of science fiction that will explore the architectural implications of giving shape to a finite environment and its impact on the complex and ever changing lives of the inhabitants over successive generations. This thesis examines the implications and limitations of space travel but also casts light on our terrestrial understanding of the roots of architectural thinking.

This thesis proposes the design of a space exploration vessel capable of sustaining a community of 2000 inhabitants that will leave Earth and never return. The unique mission criteria will allow for the in depth study of fundamental architectural issues such as confinement, permanence, habitability, and wellbeing. The vessel, named Horizon, will address the social, cultural, and environmental systems necessary for maintaining a platform for an evolving community. Emphasis throughout the thesis will be placed on the human condition and social systems rather than technical details and specifications of the ship’s construction. A human settlement travelling through the void of space and severing its ties with Earth creates an intense design challenge. How can architecture create a stimulating and humane environment without a traditional sense of site or any of the Earthly conditions that can influence memory, stimulate growth, and sustain culture? The final presentation of the thesis will take the form of an illustrated narrative. This form of representation will allow for the blending of fact and fiction, producing a narrative in the tradition of science fiction that will explore the architectural implications of giving shape to a finite environment and its impact on the complex and ever changing lives of the inhabitants over successive generations. This thesis examines the implications and limitations of space travel but also casts light on our terrestrial understanding of the roots of architectural thinking.

Vnímání zemských hranic a jejich role v členění geografického prostoru: irsko-britská a česko-německá hranice v letech 1750-1850 Abstrakt Martina Power Tato práce analyzuje vnímání zemských hranic a prostoru za pomoci srovnání německých cestopisů Čechách a britských cestopisů o Irsku publikovaných mezi lety 1750 až 1850. Obě země mají multietnický a multikulturní charakter, historicky a geograficky definované zemské hranice a jsou ve sledovaném období součástí větších nadnárodních politických celků. Význam a vnímání těchto politických příslušností je zkoumán především s ohledem na sílící integrační tendence vycházející z centra těchto celků. Zohledněno není pouze vnímání hranic politických, ale také vnímání hranic geografických, či "přirozených" (moře a hory) a hranic kulturních. U reprezentací Čech a Irska je předpokládáno, že významné místo mezi kulturními hranicemi budou zaujímat hranice konfesionální, jazykové, etnické, hranice mezi různými typy aglomerací (města a venkov), mezi různými krajinnými typy (hory a nížina) a kvalitativní hranice mezi chudobou a prosperitou. Ačkoli se přítomnost kulturní hranice do jisté míry odráží také do fyzické podoby prostoru, je její konstrukce produktem mysli a vnímání jedince, cestovatele, který se v prostoru pohybuje. Při využití cestopisů k rozkrytí významů, které...

Control algorithm is developed for a satellite with flexible appendages to achieve a good pointing performance. Detailed modeling activity was carried out that consists of sensor and actuator models, disturbances and system dynamics. Common hardware found in the spacecraft such as reaction wheels, gyroscopes, star trackers etc. were included in the model. Furthermore, the Newton-Euler method is employed for the derivation of multi-body equations of motion. Evaluation of the pointing accuracy with proper pointing performance metrics such as accuracy, jitter and stability during slew maneuvers are obtained through simulations. Control strategies are proposed to improve pointing performance.

Recent developments in technology are changing the trend both in satellite design and application of that technology. As the number of small satellites built by experts from academia and private companies increases, more effective ways of inserting those satellites into orbit is needed. Among the various studies that focus on the launch of such small satellites, research on design of Launch Vehicle tailored for nano-satellites attracts special attention. In this thesis, Multiple Cooling Multi Objective Simulated Annealing algorithm is applied for the conceptual design of Launch vehicle for nano-satellites. A set of fitness functions are cooled individually, and acceptance is based on the maximum value of the acceptance probabilities calculated. Angle of attack and propulsion characteristics are employed as optimization parameters. Algorithm finds the optimum trajectory as well as the design parameters that satisfies user defined constraints. In this study burnout velocity, and payload mass are defined as objectives. The methodolgy is applied for different design scenarios including multistage, air and ground launch vehicles.

This thesis addresses the orbit transfer optimization problem of a spacecraft. The optimal orbit transfer is the process of altering the orbit of a spacecraft with minimum propellant consumption. The spacecrafts are needed to realize orbit transfer to reach, change or keep its orbit. The spacecraft may be a satellite or the last stage of a launch vehicle that is operated at the exo-atmospheric region. In this study, a genetic algorithm based orbit transfer method has been developed. The applicability of genetic algorithm based orbit transfer method has been verified using orbit transfers which are optimal at specific cases. The solution to orbit transfer problem is also searched using steepest descent algorithm.While genetic algorithm can reach the optimal solution, steepest descent algorithm can reach optimal solution when a good initial prediction is provided. The effects of the initial orbital values on the orbit transfer solutions are also studied.

In this thesis, the kinematic properties of Single Gimballed Control Moment Gyroscopes (SGCMGs) are investigated. Singularity phenomenon inherent to them is explained. Furthermore, existing steering laws with their derivations are given. A novel steering law is developed that may provide singularity avoidance or may be used for quick transition through a singularity with small torque errors. To avoid singularity angular momentum trajectory of the maneuver is to be simulated in advance for the calculation of singularity free gimbal histories. The steering law, besides accurately generating required torques, also pushes the system to follow trajectories closely if there is a small difference between the planned and the realized momentum histories. Thus, it may be used in a feedback system. Also presented are number of approaches for singularity avoidance or quick transition through a singularity. The application of these ideas to the feedback controlled spacecraft is also presented. Existing steering laws and the proposed method are compared through computer simulations. It is shown that the proposed steering law is very effective in singularity avoidance and quick transition through singularities. Furthermore, the approach is demonstrated to be repeatable even singularity is encountered.

In this thesis, application of linear control methods to control the attitude of a Low-Earth Orbit satellite is studied. Attitude control subsystem is first introduced by explaining attitude determination and control components in detail. Satellite dynamic equations are derived and linearized for controller design. Linear controller and linear quadratic regulator are chosen as controllers for attitude control. The actuators used for control are reaction wheels and magnetic torquers. MATLAB-SIMULINK program is used in order to simulate satellite dynamical model (actual nonlinear model) and controller model. In simulations, the satellite parameters are selected to be similar to the actual BILSAT-1 satellite parameters. In conclusion, simulations obtained from different linear control methods are compared within themselves and with nonlinear control methods, at the same time with that obtained from BILSAT-1 satellite log data.

Systems Engineering methodology applied to the development of an In Situ Propellant Production system in Mars.