The topic of this diploma thesis is design of a tugboat. The thesis concerns designing a tugboat while meeting basic technological, ergonomic, ecologic and aesthetic requirements while using modern technologies and manufacturing options. There is an emphasis on innovative and unconventional solution, which will differ from contemporary products.

<p>A literature search was conducted to determine to the type and scope of decision methodologies employed in selection of a ship propulsion plant by the commercial and naval shipbuilding communities as well as methodologies used in other industries. The methodologies were categorized and evaluated by the author with regard to ability to accommodate multi-attribute decision-making involving attributes of a qualitative and quantitative nature inherent in propulsion plant selection.</p> <p> An alternative decision methodology employing the analytical hierarchy process (AHP) combined with selection criteria and sub-criteria unique to the shipbuilding industry was proposed which offers improvements in consistency and quality of judgements and accountability over current methodologies. A case study involving a 700 foot RoRo vessel design was developed to demonstrate how the alternative methodology could be applied. A three level decision hierarchy was developed to evaluate four propulsion plant alternatives involving gas turbine, low speed diesel and medium speed diesel prime movers.</p> <p> The results obtained using the proposed methodology were analyzed and sensitivity analyses were prepared assessing the range of sub-criteria weights assigned by the author over which the plant selection would be valid. A description of the investigation, selection criteria and sub-criteria, benefits, and recommendations for future efforts is included.</p> / Master of Science

A hybrid thruster system utilizes propellants in two different stages, traditionally a solid fuel and a gaseous or liquid oxidizer. Recently hybrid thrusters have become a popular topic of research due to the high demand of a ”green” replacement for hydrazine. Not only are hybrid thruster systems typically much safer than hydrazine, but they are also a low-cost system with a high reliability in performance. The Propulsion Research Laboratory (PRL) at Utah State University (USU) has developed a hybrid thruster system using 3-D printed acrylonitrile butadiene styrene (ABS) as the fuel and gaseous oxygen (GOX) as the oxidizer. This system has been spaceflight flown and tested in a hard vacuum environment with success. However, GOX has a low density and must be stored at high pressures to be considered viable. This thesis investigates the use of N2O/O2 mixtures, ”Nytrox”, and more commonly known as ”laughing gas”, as a higher density replacement oxidizer for GOX. Ina manner directly analogous to the creation of soda-water using dissolved carbon dioxide, Nytrox is created by bubbling gaseous oxygen under high pressure into nitrous oxide until the solution reaches saturation level. Oxygen in the mixture ullage dilutes the nitrous oxide vapor, and increases the required decomposition activation energy of the fluid by several orders of magnitude. Data from tests using each oxidizer are analyzed and presented for performance comparisons. Comparisons include, ignition reliability, ignition energy, thrust coefficient, characteristic velocity, specific impulse, and regression rate. Nytrox is shown to work effectively as a “drop in” replacement for gaseous oxygen, exhibiting slightly reduced specific impulse and regression rate, but with the trade of a significantly higher volumetric efficiency.

Many electrically propelled, and magnetically levitated and guided actuation systems (maglev) use either linear induction or synchronous machine topologies. From the cost, reliability, fault tolerance, and phase independence points of view, linear switched reluctance topologies are attractive for transportation application. This thesis investigates a novel topology in which a linear switched reluctance machine (LSRM) propulsion drive is incorporated in the magnetically levitated and guided vehicle. Designs of the LSRM and dc electromagnet, analytical aspects of modeling and dynamics of the vehicle, and closed loop control of propulsion, levitation, and guidance systems are discussed with comprehensive simulations and experimental results. Due to the lack of standard design procedure for LSRM, a novel design procedure is proposed using the current knowledge and design procedure of rotating switched reluctance machines. Analysis procedures for the phase winding inductance, propulsion and normal forces with translator position are developed with a lumped-parameter magnetic circuit model and the results from it are verified with two-dimensional finite element analysis. Extensive experimental correlation of inductance, propulsion and normal forces to validate the analysis and design procedure is presented. For the stable operation of the electromagnetic levitation and guidance systems, which have inherent unstable characteristics, the air gap position and force/current control loops are designed using PID (or PD) and PI controllers, respectively, and implemented and tested. The step-by-step design procedures for each controller are systematically derived. A feedforward compensation strategy for the levitation air gap control is proposed to reject the external force disturbance mainly caused by the normal force component generated in the LSRM propulsion drive system. The reduction of mechanical vibration and hence the enhancement of ride quality is achieved. Extensive dynamic simulations and experimental results for the integrated maglev system are presented with a 6 m long prototype system. Experimental correlation proves the validity of the controller design procedure based on the single-input and single-output model, and shows the feasibility of the LSRM-propelled electromagnetic levitation and guidance systems. A novel maglev topology in which only two sets of LSRMs are utilized to control individually propulsion, levitation, and guidance forces is proposed. One set of the linear switched reluctance actuator produces the levitation and propulsion forces and the other set generates the propulsion and guidance forces. The proposed architecture, thereby, obviates the need for design, development, and implementation of separate actuation systems for individual control of propulsion, levitation, and guidance forces and in contrast to most of the present practice. Further, the proposed system utilizes each of the linear switched reluctance actuation system for producing the propulsion force, thereby giving an overall high force density package for the entire system. The feasibility of the proposed system by finite element analysis is demonstrated. / Ph. D.

No description available.

This thesis studies competence of simplified simulation methods for boosting simulation.  The most efficient propulsion unit has higher amount of power compared to less efficient propulsion units in boosting. Boosting is relevant subject to study due to new concept. New concept allows a larger diameter for the propeller which increases the efficiency of the propeller. New concept relies on the idea to have the propeller behind the hull.   The thesis is restricted to study displacement hulls from a point of view of propulsion efficiency. Large cruise ship model is utilized in this thesis to identify boosting related effects efficiently. Model tests reports of this concept are used as a baseline and a comparison material for two methods that are tested in this thesis. These methods are Matlab simulation code and OpenFOAM as the CFD software.   New propulsion arrangement concept is more efficient than current solutions for this hull type according to model tests. Trend of the CFD and Matlab simulation results matches well with model test results for boosting. Matlab simulation is evidently more time efficient solution than CFD simulation for boosting. Simplified CFD simulation is sufficiently accurate to study boosting concept with this research setup. Matlab and CFD simulations can be combined to obtain the most efficient solution to analyze the most effective load division for boosting.   Different types of hulls should be simulated and results should be verificated with model or full scale tests. In addition, ships with old two shaft arrangements could be converted to have two smaller pods and center line propeller in order to have better comparison with current methods. Scaling factors increases the uncertainty for new concepts; therefore full scale measurements are required. / Denna masteruppsats studerar möjligheterna med förenklade simuleringsmetoder i relation till nya framdrivningskoncept. Studerat koncept ger möjlighet till en större diameter för en boosterpropeller i centerlinjen, vilket ökar propellerns effektivitet. Konceptet bygger på tanken att få propellern bakom skrovet. Masteruppsatsen är begränsad till att studera deplacerande skrov i relation till framdrivningseffektiviteten. Studien appliceras på stora kryssningsfartyg. Resultat från modellförsök används som en referens och ett jämförelsematerial för de två beräkningsmetoder som testas i denna masteruppsats. Dessa metoder är Matlab-simuleringskod och OpenFOAM som CFD-programvara. Arbetet visar att det nya framdrivningskonceptet är effektivare än nuvarande lösningar för denna skrovtyp. Resultaten från CFD och simuleringsresultat från Matlab matchar väl med modellprovresultat. Matlab-simulering är en mer tidseffektiv lösning än CFD-simulering. Förenklad CFD-simulering är tillräckligt exakt för att studera boosterkoncept. Matlab- och CFD-simuleringar kan kombineras för att få den mest effektiva lösningen och för att analysera den mest effektiva belastningsfördelningen mellan propulsorer. Olika typer av skrov bör undersökas och resultaten ska verifieras med modell- eller fullskaletester. Skaleffekter ökar osäkerheten, därför krävs fullskalemätningar

With the advent of smaller satellites, along with the need for less than 0.1 μN precision attitude control for interferometry and imaging missions, finer micro- to sub-micro- thrusters have become an area of high interest. As thrusters are developed and ground-tested, it is necessary to evaluate their thrust performance on-orbit. On-orbit measurements offer actual thrust performance in mission conditions, free from ground facility vibrations and miniaturization restraints, and allow a thruster system to achieve a NASA Technology Readiness Level (TRL) of 7-8. A review is conducted of existing and proposed ground and on-orbit thrust measurement techniques. Experimental gaps and complementary methods are examined along with the current thrust resolution limits. A novel fusion technique combining attitude determination, torsional balance, and filtering techniques is proposed to increase resolution beyond current on-orbit minimums, 4μN, via a dedicated sub-μN on-orbit thrust measurement mission. A simulated case study in the application of this measurement technique to a theoretical Casimir-thruster-equipped, 10-7-10-13 N, smallsat mission is explored. A detailed error analysis is conducted, and the technique is found to be analytically viable for greater than or equal to 10-7 N on a 1U nanosat equipped with sun sensor and three-axis gyroscope, as well as physically viable at a TRL 7-9 level. Recommended next steps are modification of the post-processing technique to decrease gyroscope noise and mass restrictions or exploration of suggested alternate methods, including orbit estimation, direct force sensing, and formation flying.

This thesis aims to uncover preliminary design relationships for an inlet of a split-wing electric distributed propulsion regional airliner. Several aspects of the inlet design were investigated, including: the overall thickness of the airfoil section with respect to the chord, inlet throat area, and lip radius. These parameters were investigated using several angles of attack and mass flow rates through the fan. Computational fluid dynamics, with a 2nd Order turbulence model was used and validated against World War II era data from NACA, as those studies were the most pertinent wind tunnel data available. Additionally, other works by Boeing, Empirical Systems Aerospace (ESAero), Rolling Hills Research, and the Air Force Research Laboratories (AFRL) were considered as part of this design tool tradespace. Future work considerations include utilizing an airfoil section designed for M = 0.6 or 0.65 cruise conditions as opposed to a symmetrical airfoil section, extruding the 2-D airfoil section discussed in this thesis for 3-D effects, and incorporating fan rotational physics into the simulations to better account for inlet Mach number effects.

The objective of this project is to present a Lithium Ion battery voltage model derived using systems engineering principles. This paper will describe the details of the model and the implementation of the model in practical use in a power system. Additionally, the model code is described and results of the model output are compared to battery cell test data. Finally, recommendations for increased model fidelity and capability are summarized. The modeling theory has been previously documented in the literature but detailed implementation and application of the modeling theory is shown. The detailed battery cell test voltage profiles are proprietary; as such this project will not include axis values, often used in presentation of proprietary data in the public domain. The objective of this presentation is still achieved, as the modeling implementation and results are clearly demonstrated.

The performance and stalling behavior of an axial-flow compressor subjected to several different inlet distortion patterns was investigated. The effect of inlet distortion on overall compressor performance was determined through the measurement of compressor characteristics for each inlet flow condition. Dynamic pressure transducers were employed to investigate rotating stall cell behavior during the inception of stall. Rotor blade response to distorted inflow was measured in the form of average blade pressure profiles by using a scanning valve. Results indicated a substantial reduction in total pressure rise capability for distorted operation. A 25 per cent loss in stall pressure rise was observed for the most severe distortion level. The stall cell was found to rotate in the direction of rotor motion, but at one-half the rotor speed. The cell encompassed the rotor blade tip region down to approximately midspan. During the onset of stall, the circumferential extent of the cell was observed to vary from 60 to 80 degrees. At the rotor blade tip the stall cell relative pressure fluctuations indicated zero flow through the cell. The amplitude of the stall cell was attenuated in the distorted flow region due to the lower air velocity behind the distortion screens. Rotor blade suction side pressure measurements indicated that increasing the circumferential extent of distortion above some "critical" value induced blade stall at higher flow rates. For the low speed compressor used, it appears that the critical angle phenomena is a function of compressor design and is independent of distortion level. / Master of Science