The McTronX Research Group at the North-West University is conducting research in the field of Active Magnetic Bearings (AMBs) with the aim of establishing a knowledge base for future industry consultation. AMBs are environmentally friendly and are a necessity in the pebble bed modular reactor (PBMR), a South-African initiated project, which is predicted to be the means of supplying Africa and many other countries with modular energy in the future. Aside from the PBMR, there are numerous other AMB industrial applications. The aim of this project is to develop a comprehensive AMB model that considers the effect that rotor dynamics has on an AMB system. This model is used to analyse a double radial AMB, capable of suspending a rigid- and flexible rotor, to explain previously noticed phenomena. Two modelling methods are focussed on namely the System Matrix Method and Transfer Matrix Method (TMM) both of which are implemented in MATLAB®. The rigid rotor model is firstly implemented as a point mass in state-space form followed by use of the TMM to analyse its bending modes. The stability and critical speeds of the system are analysed due to a change in the supports' properties along with rotor gyroscopy and its effect on the system. During analysis of the flexible rotor the TMM was used via a similar approach as was followed with the rigid rotor. The results indicate that the system is experiencing lower than expected damping due to the model that is used within the control loop. The previously assumed rotor model in the control loop is not sufficient to describe its complex behaviour. This causes the unexpected damping characteristics. This project suggests future work to be conducted in expanding the frequency domain model of the rotor within the control loop to account for its physical shape. / Thesis (M.Ing. (Computer and Electronical Engineering))--North-West University, Potchefstroom Campus, 2009.

The McTronX Research Group at the North-West University is conducting research in the field of Active Magnetic Bearings (AMBs) with the aim of establishing a knowledge base for future industry consultation. AMBs are environmentally friendly and are a necessity in the pebble bed modular reactor (PBMR), a South-African initiated project, which is predicted to be the means of supplying Africa and many other countries with modular energy in the future. Aside from the PBMR, there are numerous other AMB industrial applications. The aim of this project is to develop a comprehensive AMB model that considers the effect that rotor dynamics has on an AMB system. This model is used to analyse a double radial AMB, capable of suspending a rigid- and flexible rotor, to explain previously noticed phenomena. Two modelling methods are focussed on namely the System Matrix Method and Transfer Matrix Method (TMM) both of which are implemented in MATLAB®. The rigid rotor model is firstly implemented as a point mass in state-space form followed by use of the TMM to analyse its bending modes. The stability and critical speeds of the system are analysed due to a change in the supports' properties along with rotor gyroscopy and its effect on the system. During analysis of the flexible rotor the TMM was used via a similar approach as was followed with the rigid rotor. The results indicate that the system is experiencing lower than expected damping due to the model that is used within the control loop. The previously assumed rotor model in the control loop is not sufficient to describe its complex behaviour. This causes the unexpected damping characteristics. This project suggests future work to be conducted in expanding the frequency domain model of the rotor within the control loop to account for its physical shape. / Thesis (M.Ing. (Computer and Electronical Engineering))--North-West University, Potchefstroom Campus, 2009.

En aérospatial, les contraintes de masse ont conduit à utiliser des structures plus légères et par conséquent plus souples, induisant de nouveaux objectifs de commande, comme la réduction des efforts structuraux. Pour satisfaire ces objectifs, les modes de flexion doivent être considérés dès la synthèse de la loi de commande, ce qui entraîne certaines contraintes comme les non linéarités, le sous actionnement et l’altération des mesures par les modes souples. En considérant ces contraintes, cette thèse traite de la synthèse d’une méthode de commande non linéaire pour les systèmes aérospatiaux souples. Nous nous intéressons particulièrement au problème d’atténuation des oscillations provoquées par les modes souples. Pour cela, nous définissons une classe de système non linéaire, sous actionnée et à minimum de phase, représentative des systèmes aérospatiaux souples. Pour cette classe de système, nous proposons une loi de commande non linéaire synthétisée par retour d’état en utilisant des changements de variables et la technique du backstepping. La synthèse est effectuée de façon à améliorer le régime transitoire des modes souples. Les états souples n’étant pas mesurés, le problème du retour de sortie est également traité par l’intermédiaire d’observateurs adaptatifs (à temps fini et asymptotique). Des incertitudes sur la pulsation et l’amortissement des modes souples sont en particulier considérées. La méthode proposée est illustrée par des simulations numériques réalisées sur un lanceur et un avion hypersonique. / Due to mass constraints aerospace systems tend to have lightweight and flexible structures leading to new control objectives such as structural load reduction. To fulfil these objectives, flexible modes must be considered from the design of the controller, requiring to consider some constraints such as nonlinearities, underactuation, or measurement corruption terms. Consider these constraints, this thesis treats the design of a nonlinear control method for flexible aerospace systems. We particularly focus on the problem of reducing oscillations caused by the bending modes. To do that, we define a class of nonlinear system which is both underactuated and minimum phase and that represents flexible aerospace systems. Consider this class, we propose a nonlinear full-state controller based on changes of coordinates and the backstepping technique. The control design is carried out to enhance the transient of the flexible modes. Flexiblestates being not measured, the output-feedback problem is also treated through adaptive observers (finite-time and asymptotic). Uncertainties of natural damping and frequency of the bending modes are particularly considered. The proposed method is illustrated by numerical simulations performed on a space launch vehicle and an hypersonic aircraft.

Internal combustion engines are used in many applications. The same engine type may have different components mounted to it depending upon its use. These engine mounted components need to be designed against fatigue in order to withstand the engine vibrations. Measured engine vibrations are commonly used as input data for fatigue estimation. The focus in this thesis is set on heavy-duty diesel engines, typically used in trucks, buses and industrial applications. All of the appended papers use engine vibration measurements to evaluate the proposed methods. In Paper A, the engine block motion is described with a seven degree of freedom kinematic model. These degrees of freedom consist of six rigid body modes and one assumed twisting degree of freedom. With this description, measured engine block vibrations can be used to accurately predict the vibration in positions that have not been measured. Relating the measured vibrations of an engine mounted component with the projected motion of the engine block at that same position, makes it possible to identify local dynamic phenomena. In Paper B, the kinematic model of Paper A is extended with three assumed bending deformation mode shapes. For the current engine type, all of the assumed deformation modes are ranked within the 10-300 Hz frequency range. The deformation mode of highest importance is the engine block twist. Including bending deformation increases the accuracy of the engine block vibration description but it also increases the demands on instrumentation. In Paper C, the possibility to modify measured engine vibration signals, for addition or removal of engine mounted components, is investigated. For this purpose, engine vibration measurements were performed with and without a 29 kg brake air compressor mounted to the engine. For the task of removing the effect that this engine mounted component has on the engine block, the two cases of knowing, and not knowing the vibration of the component are both considered. The proposed methodology successfully predicts the changes in engine vibration due to system modification. The proposed method can also be used to estimate the time response of a component's centre of gravity. In this study the component's dynamic properties are derived from measurements but they could also be produced using finite element analysis. This can be useful early in the design process to find critically stressed areas due to base excitation. / <p>QC 20171222</p>