Shape memory alloys are new, functional materials used in actuator applications with their high power to weight ratio. The high strength or displacement usage of shape memory alloys makes them suitable for direct drive applications, which eliminate use of power transmission elements. The aim of this research is to develop the methodology and the necessary tools to design and produce linear shape memory alloy actuators to be used in missile systems, space applications, and test equipments. In this study, the test apparatus designed and built to characterize shape memory alloy thin wires is described, and then the characterization tests, modeling and control studies performed on a wire are explained. In the control studies, displacement control through strain, resistance and power feedback is investigated and different control strategies (proportional-integral, proportional-integral with feedforward loop, and neural network) are employed. The results of the characterization tests, simulations and experiments are all presented in graphical and tabular form. From the results it is concluded that through careful characterization, the behavior of SMA wire can be closely approximated through models which can be used effectively to test various control strategies in simulations. Also, satisfactory position control of SMA wires can be achieved through both classical and NN control strategies by using appropriate feedback variables and power is found to be a viable feedback variable. Lastly, a linear SMA wire actuator is designed as a case study. The actuator prototype is produced, suitable control strategies are applied and actuator is experimented to validate the theoretical assumptions. The actuator developed through this work is a technology demonstration and shows that shape memory alloy elements can be utilized in several defense and space applications contracted to T&Uuml / BiTAK-SAGE as well as certification test equipments. The development of shape memory alloy actuators that can be used in defense and later in aeronautical/space applications is a critical research and development project for national defense industry.

Das Hauptmerkmal eines fehlertoleranten Regelungssystems ist die Aufrechterhaltung der Gesamtsystemstabilität und einer akzeptablen Leistung angesichts von Fehlern und Ausfällen innerhalb des Systems. In dieser Arbeit wird ein Verfahren zur Fehlererkennung und Ansätze der fehlertoleranten Regelung (FTR) mit einer Anwendung gegen Aktorfehler von Regelungssystemen, die aus sowohl einem einzelnen Aktor als auch mehreren Aktoren (z.B. Softrobotik) bestehen, vorgestellt. Diese Methode beruht hauptsächlich auf einem Index, genannt Fitnessindex (FI. Der FI wird durch den Vergleich der aktuellen Parameter des Aktors und die im Normalzustand mittels eines Modells geschätzt. Die Ergebnisse des Fitnessindex werden mit Hilfe des Performanceindex verwendet zur Bewertung des Schweregrades eines Aktorfehlers während des Betriebes in einem geschlossenen Regelkreis und sind die entscheidende Grundlage zur automatischen Fehlerdetektion, Fehlerdiagnose und der anschließenden FTR. Diese Methode wird in einem Simulationsmodell getestet, das dem Versuchsaufbau eines Formgedächtnislegierungs-Aktors entspricht. Die Simulationsergebnisse zeigen die Berechnungsergebnisse über den FI und anschließend die Verwendung der Ergebnisse des FIs zur Durchführung der FTR, um die Leistung zu gewährleisten und die Zuverlässigkeit der Regelungssysteme zu verbessern, wenn ein Fehler im Aktor auftritt. / The main feature of a fault tolerant control system is to maintain overall system stability and acceptable performance in the face of errors and failures within the system. In this thesis, a method for fault detection and approaches of the fault tolerant control (FTC) with an application against actuator errors of control systems, which consist of a single actuator as well as several actuators (soft robotics), is presented. This method is mainly based on an index called the fitness index (FI). The FI is estimated by comparing the current parameters of the actuator and in the normal state, based on a model. The results of the fitness index are used with the help of the performance index to evaluate the severity of an actuator fault during an operation in a control loop and are the decisive basis for automatic fault detection, fault diagnosis and subsequent the FTC. This method is tested in a simulation model that corresponds to the experimental setup of a shape memory alloy actuator. The simulation results show the calculation results about the FI and in addition the use the results of the FI to perform the FTC in order to ensure the performance and improve the reliability of the control systems when a fault occurs in the actuator.

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