Remotely Operated underwater Vehicles (ROVs) are getting more and more advanced withevery new model. As new functionality is added, the price increases. This thesis is one partof a larger project, where the goal is to develop a low-budget ROV. The ROV should later bemade autonomous and entered into a competition.This thesis have focused on the modeling and stabilizing control of an ROV that was designedby mechanical engineering students at Linköping University. The only sensor used was anInertial Measurement Unit (IMU) and the ROV has a torpedo-like design. The modeling wasdone using identification in Matlab with the grey box and black box methods. Water trialsand simulations show that the model is estimated sufficiently good to be used as the basis ofdifferent model based controllers.Two different control strategies were implemented; a linear quadratic controller (LQ) and amodel predictive controller (MPC). Both controllers worked desirably in simulations. Onlythe LQ controller was evaluated in real world tests. Due to problems with the implementationenvironment chosen for the MPC, the MPC could not be tested.The thesis also uses decision matrices as a mean to motivate the important decisions thathave been made.

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In radiotherapy with protons, a constant relative biological effectiveness (RBE) of 1.1 is traditionally applied, i.e. protons are assumed to be 10\% more effective than photons in killing cells. This constant RBE is however being questioned, as an abundance of in vitro studies indicate a variable RBE with particle energy, and as in vivo studies also show unexpected toxities near proton track ends, thereby indicating that a variable RBE might also be present clinically. Variable RBE is in turn typically described by a model. For protons, the vast majority of suggested models are based on the linear quadratic (LQ) model, where an expression for RBE is derived by comparing the dose from protons and a reference radiation (typically photons) to achieve a desired survival fraction. The parameters for the model are subsequently obtained by fitting parameters of the derived expression to in vitro data, where the survival fraction of cells has been determined as a function of dose and an averaging over the fluence spectrum of linear energy transfer (LET). While the beam quality parameter typically is the averaged LET, how the averaged LET value has been calculated or determined has often not been fully provided, possibly introducing a source of error in the estimated RBE value. This can vary with respect to the averaging method (typical dose- or track averaging), included particles (only primary, or also including secondaries) and other aspects. Furthermore, while LET is the most commonly used beam quality descriptor, other quantities exist such as Q and z*2/β2 , here renamed as Qeff. These alternative metrics have been shown to better correlate with RBE across different particle species compared to LET, and can possibly also perform better for a single particle species. However, this has so far not been systematically tested or verified. Paper I investigates which kind of averaged LET is provided in the scientific literature for the purpose of RBE determination, for both protons and other hadronic particles. It also attempts to quantify the corresponding impact to the calculated RBE values. Paper II investigates which beam quality descriptor is most suitable for predicting RBE by simulating the experimental setup of recently published high throughput in vitro cell survival studies for RBE determination by a Monte Carlo particle transport code, and fitting parameters to a phenomenological LQ-based model based on the cell survival data. Different variations of LET, Q and Qeff are included, to generate both linear and non linear variable RBE models. In paper I, it is shown that averaged LET for the purpose of RBE determination is, typically, not entirely well defined with a significant minority not mentioning which averaging method is used, and a majority not mentioning what particles are included when averaging. The corresponding impact to the RBE for protons is, in most cases, small, unless heavier secondary particles are included. In paper II it is shown that Q and especially Qeff are expected to better predict RBE compared to LET by a statistically significant margin, for both linear and non-linear models, suggesting they are likely to be more suitable beam quality descriptors to use in a LQ based phenomenological variable RBE model.

La forte et rapide croissance de l’énergie éolienne à travers le monde a nécessité la mise en vigueur de nouveaux critères normalisés permettant de l’intégrer dans les réseaux électriques sans affecter la qualité et la stabilité du système, et qui peuvent demander aux éoliennes de participer au réglage de la fréquence dans les réseaux en cas de besoin. Ainsi, les travaux présentés dans cette thèse visent à proposer une solution de loi de commande qui permette aux éoliennes de participer au réglage de la fréquence du réseau. En analysant les limites des correcteurs classiques de types P, PI et PID, nous avons opté pour la commande LQ munie d’une approche multimodèle et qui a montré de bonnes performances aux résultats de simulation. Certaines améliorations ont été ajoutées à cette loi de commande du genre modèle de référence, action intégrale, … afin de permettre une poursuite de puissance autour d’une référence donnée qui change selon la fréquence du réseau / The fast and big growth of wind power around the world required the implementation of new standardized criteria to integrate this kind of energy into electric networks without affecting the quality and stability of the system. These criteria could ask the wind turbines to participate in the network frequency control when necessary. Thus, the works presented in this thesis aim to provide a control law solution that allows wind turbines to participate the grid frequency control. By analyzing the limits of traditional regulators such as P, PI and PID, we opted for the LQ controller combined to a multi-model approach because of the good performances shown in the simulation results. Some improvements were added to this control law: reference model, integral action, ... to allow a power trucking for a given reference that changes with the grid frequency

<p>This master thesis was carried out at the Department of Aerodynamics and Flight Mechanics at Saab Aerosystems, Linköping, Sweden. It makes up the author’s final work prior to graduation in the field Applied Physics and Electrical Engineering at the Department of Electrical Engineering at The Linköping Institute of Technology (LiTH), Linköping, Sweden.</p><p> </p><p>The objective of the paper was to study a non-uniform helicopter rotor downwash model in forward flight for the unmanned helicopter Skeldar, which is under development at Saab. The main task was to compare the mentioned model with today’s uniform downwash model in order to find differences and similarities. This was done both from a modeling and a controlling perspective. To start with, an introduction is given which is followed by a helicopter theory chapter. The following three chapters deal with the theory of induced velocity, the helicopter model and the Linear Quadratic Regulator (LQR). Finally, the results are presented and discussed.</p><p> </p><p>The downwash models were derived using Momentum Theory (MT) and Blade Element Theory (BET). These two theories were combined in order to find a connection between the induced velocity and the rotor thrust coefficient. The non-uniform downwash model that was studied is proposed by Pitt & Peters and describes a linear variation of the induced velocity in the longitudinal plane.</p><p> </p><p>For the control, a LQ-regulator was chosen since it is easily implemented in MATLAB and it stabilizes the plant model by feedback and consequently creates a robust system. Before the controller could be implemented, the models had to be reduced and the states had to be divided into longitudinal and lateral ones.</p><p> </p><p>The comparison between the open systems clearly shows that differences in the inflow models propagate to all states and consequently the helicopter behaves differently in all planes. Great discrepancies are apparent for the angular velocities <em>p</em> and <em>q</em>. For Pitt & Peters’ model those states are believed to be strongly affected by the system’s positive real pole, causing a rather unstable behavior. When the systems were closed by feedback, the differences were reduced dramatically. Pitt & Peters’ model resulted in greater overshoots than the uniform model, but the overall behavior of all states was rather similar for the two models.</p><p> </p><p>It is concluded, that the adaption of Pitt & Peters’ inflow model does not make any substantial difference when a controller is implemented. The differences between the open systems, however, are reason enough to question Pitt & Peters’ model. In order to evaluate the non-uniform model properly, it has to be compared to suitable flight data which is still lacking up to this date.</p>

<p>The ducted fan UAV is an unmanned aerial vehicle consisting mainly of a propeller enclosed in a open ended tube. The UAV has the same basic functions as an ordinary helicopter UAV but has several advantages to the same.</p><p>This thesis aims to estimate the performance of the concept of the ducted fan UAV. The company where this thesis has been written, DST Control AB, is currently investigating the economical possibilities to continue the development of this kind of UAV. This thesis shall provide DST Control AB with a theoretical as well as experimental ground for the investigation by estimation the lift capacity, position accuracy and wind tolerance.</p><p>A ducted fan UAV prototype and a mathematical model for that UAV have been developed by DST Control AB and a student project at Linköping University. The model is constructed through pure physical modeling. Several noise sources have been added to better fit the reality. Several experiments have been conducted to validate the model with satisfying results. Experiments to determine the lift capacity of the craft have also been conducted. These experiments showed a slightly smaller lift capacity than the theoretically calculated lift capacity. The wind tolerance has not been tested in experiments because of the lack of available wind tunnels but simulations have given an estimation of this tolerance.</p><p>To estimate the position accuracy, two different control systems have been implemented. The simplest control system is a system consisting of several PID controllers. The system is divided into two separate subsystems connected in cascade. The inner subsystem takes the pitch, roll and yaw angle as inputs and gives the rudder angles as outputs. The outer subsystem takes the inertial position as input and gives roll, pitch and yaw as outputs. Together, the two subsystems can be used to control the entire craft. The inner subsystem has also been replaced with a small LQ Compensator. An LQ Compensator for the entire system is also implemented giving about as good performance as the PID controller and better performance than the PID/LQ combination.</p>

This master thesis was carried out at the Department of Aerodynamics and Flight Mechanics at Saab Aerosystems, Linköping, Sweden. It makes up the author’s final work prior to graduation in the field Applied Physics and Electrical Engineering at the Department of Electrical Engineering at The Linköping Institute of Technology (LiTH), Linköping, Sweden.   The objective of the paper was to study a non-uniform helicopter rotor downwash model in forward flight for the unmanned helicopter Skeldar, which is under development at Saab. The main task was to compare the mentioned model with today’s uniform downwash model in order to find differences and similarities. This was done both from a modeling and a controlling perspective. To start with, an introduction is given which is followed by a helicopter theory chapter. The following three chapters deal with the theory of induced velocity, the helicopter model and the Linear Quadratic Regulator (LQR). Finally, the results are presented and discussed.   The downwash models were derived using Momentum Theory (MT) and Blade Element Theory (BET). These two theories were combined in order to find a connection between the induced velocity and the rotor thrust coefficient. The non-uniform downwash model that was studied is proposed by Pitt &amp; Peters and describes a linear variation of the induced velocity in the longitudinal plane.   For the control, a LQ-regulator was chosen since it is easily implemented in MATLAB and it stabilizes the plant model by feedback and consequently creates a robust system. Before the controller could be implemented, the models had to be reduced and the states had to be divided into longitudinal and lateral ones.   The comparison between the open systems clearly shows that differences in the inflow models propagate to all states and consequently the helicopter behaves differently in all planes. Great discrepancies are apparent for the angular velocities p and q. For Pitt &amp; Peters’ model those states are believed to be strongly affected by the system’s positive real pole, causing a rather unstable behavior. When the systems were closed by feedback, the differences were reduced dramatically. Pitt &amp; Peters’ model resulted in greater overshoots than the uniform model, but the overall behavior of all states was rather similar for the two models.   It is concluded, that the adaption of Pitt &amp; Peters’ inflow model does not make any substantial difference when a controller is implemented. The differences between the open systems, however, are reason enough to question Pitt &amp; Peters’ model. In order to evaluate the non-uniform model properly, it has to be compared to suitable flight data which is still lacking up to this date.

The ducted fan UAV is an unmanned aerial vehicle consisting mainly of a propeller enclosed in a open ended tube. The UAV has the same basic functions as an ordinary helicopter UAV but has several advantages to the same. This thesis aims to estimate the performance of the concept of the ducted fan UAV. The company where this thesis has been written, DST Control AB, is currently investigating the economical possibilities to continue the development of this kind of UAV. This thesis shall provide DST Control AB with a theoretical as well as experimental ground for the investigation by estimation the lift capacity, position accuracy and wind tolerance. A ducted fan UAV prototype and a mathematical model for that UAV have been developed by DST Control AB and a student project at Linköping University. The model is constructed through pure physical modeling. Several noise sources have been added to better fit the reality. Several experiments have been conducted to validate the model with satisfying results. Experiments to determine the lift capacity of the craft have also been conducted. These experiments showed a slightly smaller lift capacity than the theoretically calculated lift capacity. The wind tolerance has not been tested in experiments because of the lack of available wind tunnels but simulations have given an estimation of this tolerance. To estimate the position accuracy, two different control systems have been implemented. The simplest control system is a system consisting of several PID controllers. The system is divided into two separate subsystems connected in cascade. The inner subsystem takes the pitch, roll and yaw angle as inputs and gives the rudder angles as outputs. The outer subsystem takes the inertial position as input and gives roll, pitch and yaw as outputs. Together, the two subsystems can be used to control the entire craft. The inner subsystem has also been replaced with a small LQ Compensator. An LQ Compensator for the entire system is also implemented giving about as good performance as the PID controller and better performance than the PID/LQ combination.

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