In this thesis, two problems are studied. The first problem is to find a technique to generate a particular type of failure information in real time for large flexible space structures (LFSSs). This problem is solved by using structured residuals. The failure information is then incorporated into an existing fault tolerant control scheme. The second problem is a ``spin-off'' from the first. Although the H-infinity sliding mode observer (SMO) cannot be applied to the colocated LFSS , its ability to do robust state and fault estimation of the SMO makes it suitable to be used in an integrated fault tolerant control (IFTC) scheme. We propose to combine the H-infinity SMO with a linear fault accommodation controller. Our IFTC scheme is closed loop stable, suppresses the effects of faults and enjoys enhanced robustness to disturbances. The effectiveness of the IFTC is illustrated through the control of a permanent magnet synchronous motor under actuator fault.

In this thesis, two problems are studied. The first problem is to find a technique to generate a particular type of failure information in real time for large flexible space structures (LFSSs). This problem is solved by using structured residuals. The failure information is then incorporated into an existing fault tolerant control scheme. The second problem is a ``spin-off'' from the first. Although the H-infinity sliding mode observer (SMO) cannot be applied to the colocated LFSS , its ability to do robust state and fault estimation of the SMO makes it suitable to be used in an integrated fault tolerant control (IFTC) scheme. We propose to combine the H-infinity SMO with a linear fault accommodation controller. Our IFTC scheme is closed loop stable, suppresses the effects of faults and enjoys enhanced robustness to disturbances. The effectiveness of the IFTC is illustrated through the control of a permanent magnet synchronous motor under actuator fault.

This project deals with the relationship between Stockholm and the water, investigating its history and searching for a definition of its future. As a city, Stockholm is defined by water; it creates physical distance in the city, but at the same time visually ties it together. Looking specifically at Söder Mälarstrand, an undefined waterfront with great potential, this project seeks to understand the current state of this site and propose a new use for it. How can this urban landscape be defined to accommodate a contemporary use of the waterfront? What should such a development look like architecturally? As a research method, this project looks beyond the physical extension of the site to the images of it constantly reproduced. Without romanticizing the past, the research searches for the character of the site to find a potential for its future use. The project proposes a new use of the waterfront. The quay is widened, and the new space that is created is anchored by the addition of three new volumes programmatically linked to the existing activity on the site, while also allowing new uses in the future. This approach aims to create a more defined public space, making the site permeable.

Spacecrafts are generally equipped with high precision optical and other sensor payloads. The structures of most of the spacecrafts are light-weight, flexible and have low damping. Vibrations are often induced in the spacecraft body due to the presence of many disturbance sources such as momentum/reaction wheels, control thrusters used for attitude control and cryocoolers etc. Low damping leads to long decay time for vibrations hence during this period the spacecraft sensors cannot be used effectively. One possible solution is to isolate the precision sensor from the rest of the satellite and this strategy has been used for spaceborne telescopes and interferometers that have extremely precise positional and vibratory tolerances imposed on them in order to achieve scientific goals. Another strategy is to isolate the vibration source itself from the spacecraft body. This thesis deals with modelling, analysis and experimentation of a novel low frequency flexible space platform designed to serve as a mount for the disturbance source in order to insulate the source generated vibrations reaching critical areas of the structure. The novel space platform consisting of folded continuous beams, is light-weight and is capable of isolating vibration generated by sources such as reaction/momentum wheels. Finite element analysis of the platform is carried out for static and dynamic load cases. Simulation studies are carried out on flexible beam platform in order to firm up the design for passive vibration isolation. Modal analyses is done to simulate the response of each mode. Active control has been studied by embedding the platform’s beam elements with piezo actuators and sensors. The simulation results show that the space platform can effectively attenuate vibration and further improvement in vibration attenuation is possible with active control. Based on the analysis, a prototype low frequency platform has been designed and fabricated. An experimental validation has been done to test the usefulness of the low frequency platform to act as a mount for reaction wheels and to mitigate the vibration disturbances/effects transmitted from the reaction wheel assembly to structure. Measurements and tests have been conducted at varying wheel speeds to quantify and characterize the amount of isolation to the reaction wheel generated vibrations. The time and frequency domain analysis of test data clearly show that level of isolation is significant and an average of 13 dB of isolation is seen. The level of isolation is different for different isolators and it depends upon the isolator design and wheel speed. Forces and moments measured at the base for wheel with isolator and wheel without isolator clearly demonstrate and confirm a reduction in the disturbance levels of atleast one order. These isolators are further tested successfully for launch dynamic loads in order to confirm the design adequacy to sustain such loads. Results indicate that the flexible mounts of the type discussed in this thesis can be used for effective passive vibration isolation in spacecrafts with reaction/momentum wheels.

Un centro educativo es una de las instituciones más importes de la sociedad, ya que este es el lugar donde las nuevas generaciones adquieren todo tipo de conocimiento que les servirá para la vida adulta. Sin embargo, la arquitectura de las Instalaciones Educativas en el Perú es la menos desarrollada, encontrándose estancada en los modelos arquitectónicos del siglo XX. El propósito de este documento es presentar las bases necesarias para diseñar una Institución Educativa de inicial, primaria y secundaria en el distrito de San Juan de Lurigancho que responda a las metodologías educativas actuales y, al mismo tiempo, responda a la normatividad correspondiente que el Ministerio de Educación busca implementar. Asimismo, se trata de demostrar la importancia de incluir equipamiento complementario de uso compartido, ya sea con fines educativos, deportivos o culturales, que integren y refuercen el vínculo del colegio con el resto de la ciudad. / A school is one of the most important institutions in society, since this is the place where the new generations acquire all kinds of knowledge that will serve them for adult life. However, the architecture of the Educational Facilities in Peru is the least developed, finding itself stagnant in the architectural models of the 20th century. The purpose of this document is to present the necessary bases to design an initial, primary and secondary Educational Institution in the district of San Juan de Lurigancho that responds to current educational methodologies and, at the same time, responds to the corresponding regulations that the Ministry of Education seeks to implement. Likewise, it is about demonstrating the importance of including complementary equipment for shared use, whether for educational, sports or cultural purposes, that integrates and strengthens the school's link with the rest of the city. / Tesis

This thesis project has been conducted during a five-month research exchange visit to the Space Structure Dynamics and Control research group at University College Dublin. This report presents the design, development, and validation of a nanosatellite attitude control testbed. The testbed was designed to replicate the microgravity conditions of space by utilising an air bearing, enabling single-axis rotational motion for a 1U CubeSat-sized nanosatellite. The novel aspect of this research is the inclusion of two-degree-of-freedom, lumped-mass flexible appendages on either side of the nanosatellite, emulating a lightweight, flexible space structure. These flexible appendages were designed based on the stiffness characteristics of a deployable CubeSat solar array system found in existing literature, with exaggerated motion to amplify the measurable effects of various control approaches. The central focus of this project was the development of an avionics stack closely resembling CubeSat attitude control boards. The stack uses an STM32 microcontroller as the primary attitude control computer, and a suite of off the shelf breakout boards for sensors and wireless telemetry systems. Power, serial and I2C buses connect the attitude control board and the onboard computer board. A reaction wheel actuator controls the Euler heading attitude. The testbed was designed as an experimental platform for validating control algorithms developed through a model-based approach. Integration with the Simulink Embedded Coder toolbox allows for the compilation of Simulink models into C code, facilitating direct execution on the testbed. The testbed’s physical construction involves 3D printed ABS components, with the inclusion of load cells to measure disturbance torques from the excited flexible appendages. Results from validation experiments show that a simple PID controller causes significant excitation in the flexible appendages during a slew manoeuvre. However, the introduction of an input shaped attitude profile tailored to the natural frequency of the appendages successfully reduced the measured appendage excitation by 50%. Conversely, the force impedance wave based control approach did not show a reduction in appendage excitation, but shows promise for further developments in future work. In conclusion, the testbed has successfully achieved its predefined project objectives, albeit requiring further refinement, particularly in the telemetry down-link system. It is recommended that future work focuses on enhancement of the telemetry system, and validation of a model based approach to controller design. / Detta examensarbete har utförts under ett fem månaders forskningsutbyte vid forskningsgruppen Space Structure Dynamics and Control vid University College Dublin. Denna rapport presenterar design, utveckling och validering av en testbädd för attitydstyrning av en nanosatellit. Testbädden utformades för att efterlikna mikrogravitationsförhållandena i rymden genom att använda ett luftbärande lager, vilket möjliggör rotationsrörelse kring en axel för en nanosatellit av storleken 1U CubeSat. En unik aspekt av detta arbete är inkluderingen av två-frihet-graders, sammansatta flexibla påhängen på vardera sidan av nanosatelliten, vilket efterliknar en lätt, flexibel rymdstruktur. Dessa flexibla påhängen utformades med utgångspunkt från styvhetsegenskaperna hos ett utskjutbart CubeSat-solcellssystem som finns i befintlig litteratur, med överdriven rörelse för att förstärka de mätbara effekterna av olika styrmetoder. Det centrala fokuset för detta projekt var utvecklingen av en avionikstack som nära liknar CubeSat-attitydregleringkort. Stacken använder en STM32-mikrokontroller som primär dator för attitydkontroll och ett urval färdiga breakout-kort för sensorer och trådlös telemetri. Strömförsörjning, serie- och I2C-bussar ansluter attitydregleringkortet och omborddatorn med en reaktionshjulsaktuator som styr Euler-attityd. Testbädden utformades som en experimentell plattform för att validera styralgoritmer som utvecklats med hjälp av en modellbaserad metod. Integration med Simulink Embedded Coder möjliggör kompilering av Simulink-modeller till C-kod, vilket underlättar direkt exekvering på testbädden. Testbäddens fysiska konstruktion innefattar 3D-utskrivna ABS-komponenter med inkludering av lastceller för att mäta störningsmoment från de exciterade flexibla påhängen. Resultaten från valideringsexperiment visar att en enkel PID-regulator orsakar betydande excitation i de flexibla påhängena under en vridningsmanöver. Dock lyckades en input-formad attitydprofil som anpassats till de flexibla påhängenas naturliga frekvens framgångsrikt minska den uppmätta excitationen med 50%. Omvänt visade den kraftimpedansvågbaserade styrmetoden inte någon minskning i excitation, men visar potential för vidare utvecklingar i framtida arbete. Sammanfattningsvis har testbädden framgångsrikt uppnått sina fördefinierade projektmål, om än med behov av ytterligare förfining, särskilt i telemetrisystemet. Det rekommenderas att framtida arbete fokuserar på förbättring av telemetrisystemet och validering av en modellbaserad ansats till styrdesign.