For manufacturing enterprises, the potential of collecting large amounts of data from production processes has enabled the usage of machine learning for prediction-based monitoring and maintenance of machines. Yet common maintenance strategies still include reactive handling of machine failures or schedule-based maintenance conducted by experienced personnel. Both of which are time-consuming and costly for manufacturing enterprises. The incorporation of anomaly detection for production processes alleviates several problems connected to these resource-intensive maintenance strategies. Anomaly detection enables real-time maintenance alarms derived from the occurrence of anomalies and thereby a foundation for proactive maintenance during manufacturing. However, to realize this, one needs to investigate the correlation between machine failure and anomalies in the data. For the machine learning models, it is also of essence to handle the imbalance between failure and normal working condition data. In this work, we investigate the potential of anomaly detection to predict future tool failures of an active CNC-machine based on multivariate time series data collected through the standardized data collection protocol MTConnect. Two semi-supervised anomaly detection methods, DeepAnT and ROCKET OCSVM, were tested. Training and evaluation of the two models were conducted on three production part processes and the difference in anomaly distribution previous to failure and in the normal machine working condition was investigated. The results showed that both models, for all the investigated tool failures belonging to the three production part processes, found an abundance of anomalies preceding failure when compared to the normal working condition of the machines. For certain tool failures, the anomalies were found as far back as seven production cycles before failure, while other anomalies were mainly uncovered close to the failure. Furthermore, it was shown that both models performed optimally with 100 production cycles before tool failures excluded from training, indicating that more anomalies further back connected to failure or possible long-term degradation of machine tools could exist. Lastly, ROCKET OCSVM with RBF kernel showed greater reliability compared to the DeepAnT method in separating the normal working condition data of the CNC machine against the pre-failure data based on anomaly distribution. In conclusion, anomaly detection shows promising results in indicating future machine failure and could serve as a foundation for proactive maintenance strategies of machines. By incorporating proactive strategies, machine downtime, operator maintenance time, and resources and expenses resulting from machine failure could be reduced. / För produktionsföretag har potentialen att samla in stora mängder data från produktionsprocesser möjliggjort användningen av prediktionsbaserad övervakning och underhåll av maskiner genom maskininlärning. Ändå så utgörs fortfarande vanliga underhållsstrategier av reaktiv hantering av maskinfel eller schema baserat underhåll som utförs av erfaren personal. Båda dessa är tidskrävande och kostsamma för tillverkningsföretag. Införandet av anomali detektering för produktionsprocesser lindrar flera problem kopplade till dessa resursintensiva underhållsstrategier. Det möjliggör underhålls-larm i realtid härledda från förekomsten av anomalier, vilket skapar en grund för proaktivt underhåll under tillverkningen. Men för att möjliggöra detta måste man undersöka sambandet mellan maskinfel och anomalier i data utifrån definierade insamlingsmetod. Det är också viktigt att hantera obalansen mellan fel och normal arbetstillstånd data för maskininlärningsmodellerna. I det här arbetet undersöker vi potentialen för delvis övervakad anomali detektering för att förutsäga framtida verktyg fel hos en aktiv CNC-maskin baserat på multivariat tidsseriedata som samlats in genom det standardiserade datainsamling protokollet MT Connect. Två anomali detekterings metoder som endast tränats på normala arbetsförhållanden för maskiner testades, DeepAnT och ROCKET OCSVM. Träning och utvärdering av de två modellerna genomfördes på tre produktionsdelprocesser och skillnaden i anomali fördelning före fel och i det normala maskinens arbetstillstånd undersöktes. Resultaten visade att båda modellerna, för alla undersökta verktygsfel som hör till de tre produktionsdelprocesserna, fann ett överflöd av anomalier före fel i jämförelse med maskinernas normala arbetstillstånd. För vissa verktygsfel hittades anomalierna så långt tillbaka som sju produktionscykler före fel, medan andra anomalier huvudsakligen upptäcktes nära felet. Vidare visades det att båda modellerna presterar optimalt med 100 produktionscykler före verktygsfel uteslutna från träningen, vilket tyder på att fler anomalier tidigare än de åtta produktions cyklarna undersökta innan fel eller eventuell långvarig försämring av verktygsmaskiner kan förekomma. Slutligen visade ROCKET OCSVM med RBF som kärnfunktion större tillförlitlighet i jämförelse med DeepAnT metoden gällande att separera CNC-maskinens normala arbetstillstånd data från pre-failure-data baserat på anomali fördelning. Sammanfattningsvis visar avvikelse detektering lovande resultat för att indikera framtida maskinfel och kan fungera som en grund för proaktivt underhåll av maskiner. Genom att införskaffa proaktiva strategier kan maskinernas stilleståndstid, operatörens underhållstid samt resurser och kostnader till följd av maskinfel minskas.

This is predominantly a qualitative study on the manufacturing of micronozzles with an additive manufacturing (AM) technique, namely the laser-powered powder bed fusion (PBF-LB).  Manufacturing of micronozzles with standard microelectromechanical system technology often results in 2.5-D or close to 3-D structures and does not yield a fully rotationally symmetric nozzle. For this reason, AM can be a better solution. However, the structures obtained with PBF-LB exhibit very rough surfaces which will impair the performance of the micronozzle. To improve the surface finish electropolishing was performed on the interior walls.  Given the shape and the scale of the components, uniformity of the polishing is a challenge, calling for an inventive electrode configuration and electrolyte feed solution. The approach was to integrate an electrode on the inside of the converging part of the nozzle, to serve as a cathode for the electropolishing, already in the process, and to make the nozzle itself the vital part of the fluidic system.  With this, titanium micronozzles were manufactured with throat diameters varying between 300 and 800 μm. With the resolution of the used AM technique, it was possible to integrate the internal electrode in the micronozzles with a designed throat diameter down to 600 μm. Below this, the anode, and cathode, sometimes made contact short-circuiting the cell. Profilometry showed a decrease of the average surface roughness (𝑅𝑅𝑎𝑎) with 15-60 % for the electropolished micronozzles. The Schlieren imaging showed an exhaust that followed the throat’s axial direction and also demonstrated pressure disks and, hence, a supersonic jet exhaust. This study has shown that AM is a viable choice for manufacturing of rotationally symmetric micronozzles, and that electropolishing could be used to decrease the surface roughness on their inside uniformly with the integration of a cathode.

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Thesis (MScEng)--University of Stellenbosch, 2003. / ENGLISH ABSTRACT: The focus of this thesis is on the investigation of the functioning of a liquefied-gas thruster. Such a thruster could be used to provide secondary propulsion to a microsatellite in orbit. A general overview of the need for thrusters in micro-satellites is put forward in the introduction. Motivation for deciding to investigate a liquefied-gas system is presented. Recent developments in the field of micro-satellites are discussed as well as their relevance to the project undertaken. Fundamental background theory relevant to the engineering problems associated with the development and analysis of such a system is also presented. Computer programs were written to simulate such a liquefied-gas thruster system. The experimental work carried out to analyse the system from a practical view-point is documented. Attention is also given to the measurement and calibration techniques used to obtain experimental data. One-dimensional fully explicit transient mathematical models of the thruster system were developed to model the system using both compressed air and butane as propellants. These models were incorporated into computer programs used to simulate the transient behaviour of the system. Although it is intended to use butane as the propellant onboard a satellite, the reason for modelling and simulating a system using compressed air is because air is a convenient fluid to work with from both a theoretical and practical point of view. An experimental model of a thruster system was designed, built and tested using air and butane as propellants. Most of the model was built using perspex to allow for the observation of the two-phase behaviour of the propellant inside the system. Locally purchased components were used for the solenoid and fill valves. Readily available butane lighter fluid was used for butane testing. Self-made heating elements were used to provide heat input to the propellant. Testing was done at different back pressures ranging from 100 kPa down to 20 kPa in a vacuum chamber. Good comparison between theoretical and experimental results was obtained for air. Theoretical results for peak thrusts tended to over predict experimental results by approximately 15 % for a system exhausting to a pressure of 100 kPa. Peak thrusts as high as 0.2 N were obtained for vacuum tests conducted at an absolute pressure of 20 kPa. Peak thrusts of approximately 50 mN were achieved for experimental testing III atmospheric conditions using butane with a starting pressure of between 270 and 290 kPa. Typical average thrusts of between 20 mN and 30 mN were noted for butane testing with initial pressure of between 200 to 300 kPa. Peak thrusts of over 0.1 N were observed for vacuum testing at an absolute pressure of 20 kPa. An equation to correlate the experimentally determined average thrust as a function of pulse duration and starting pressure was developed. This correlated most of the experimental data to within ±25 %. Theoretical results for butane testing are able to predict peak thrusts within approximately 20 % for starting pressures in the range of 200 to 300 kPa. Since the project was an exploratory investigation into a liquefied-gas thruster, some additional aspects relating to such systems were also given attention. The effect of liquid propellant motion or sloshing was considered and recommendations regarding the design and placement of the propellant tanks were made. The use of heat pipes as an alternative to electrical heating elements was investigated and some elementary design aspects are presented graphically. The management of the liquid propellant using surface tension devices was examined qualitatively. Recommendations relating to future projects in the field of simple, low-cost propulsion systems for micro-satellites are put forward. More specifically these recommendations are with regard to: thermo-fluid modelling of the propellant, future experimental work to be done, techniques to measure small thrusts and vacuum chamber testing. / AFRIKAANSE OPSOMMING: Die tesis ondersoek die funksionering van 'n vervloeidegas stuwer. So 'n stuwer kan gebruik word om sekondêre aandrywing aan 'n mikro-satelliet in 'n wentelbaan te verskaf. 'n Algemene oorsig oor die behoeftes van stuwers vir mikro-satelliete word voortgesit in die inleiding. Redes vir die gebruik van 'n vervloeidegas stuwer word bespreek. Onlangse ontwikkelinge in die veld van mikro-satelliet aandrywing word bespreek asook die toepaslikheid daarvan. Fundamentele teoretiese agtergrond verbonde aan die ontwikkeling en analise van so 'n stuwer stelsel word ook gegee. Rekenaarprogramme is geskryf om die gedrag van so 'n stuwer stelsel te simuleer. Eksperimentele werk is gedoen om die stelsel vanuit 'n praktiese oogpunt te analiseer. Aandag word ook gegee aan die metings- en kalibrasietegnieke soos toegepas vir die eksperimentele werk. Eendimensionele volle eksplisiete wiskundige modelle is ontwikkelom die oorgangsgedrag van die stuwer-stelsel te simuleer met beide lug en butaan as dryfmiddel. Hierdie modelle is geïnkorporeer in die rekenaar programme om die stuwer stelsel te simuleer. Alhoewel dit beoog word om butaan as die dryfmiddel aan boord die satelliet te gebruik, is lug ook gebruik vir simulasie weens sy gerieflikheid as 'n vloeier uit beide 'n teoretiese en 'n praktiese oogpunt. 'n Eksperimentele model van die stuwer stelsel is ontwerp, gebou en getoets met beide lug en butaan as dryfmiddels. Die model is hoofsaaklik uit perspex gebou sodat die twee-fase gedrag van die butaan uitgebeeld kon word. Vrylik beskikbare butaan aansteker vloeistof IS gebruik VIr butaan toetsing. Selfvervaardigde verhittingselemente is gebruik om hitte aan die dryfmiddel te verskaf. Toetse is gedoen deur verskeie omgewingsdrukke varieërend van 100 kPa af tot 20 kPa in 'n vakuumtenk te gebruik. Goeie ooreenstemming tussen die teoretiese en eksperimentele resultate vir die toetsing van lug is verkry. Die teoretiese resultate neig om die piek stukrag 15 % hoër te voorspel as die eksperimentele resultate vir 'n stelsel wat tot 'n omgewingsdruk van 100 kPa by die uitlaat. Piek stukragte van meer as 0.2 N is gekry vir vakuum toetse wat gedoen is by 'n omgewingsdruk van 20 kPa. Tydens eksperimentele toetsing met butaan teen 'n aanvanklike druk tussen 270 en 290 kPa, in atmosferiese toestande, is piek stukragte van ongeveer 50 mN behaal. Tipiese gemiddelde stukragte van tussen 20 en 30 mN is waargeneem vir butaan toetsing teen 'n aanvanklike druk tussen 200 en 300 kPa. Piek stukragte van meer as 0.1 N is behaal vir vakuum toetse met 'n absolute druk van 20 kPa. 'n Vergelyking om die gemiddelde stukrag, wat eksperimenteel bepaal is, as 'n funksie van puls tydsduur en aanvanklike druk te korreleer, is ontwikkel. Die meeste eksperimentele data se afwyking van die korrelasie-vergelyking was minder as 25 %. Teoretiese resultate vir butaantoetse het piek stukragte binne 20 % van die eksperimenteel metings korrek voorspel vir aanvanklike drukke tussen 200 tot 300 kPa. Weens die feit dat die projek 'n oorhoofse ondersoek in In vervloeidegas stuwer behels, is aandag ook gegee aan addisionele aspekte wat verband hou met sulke stelsels. Die effek van die vloeistof-dryfmiddel se onstabiele beweging in sy tenke is in ag geneem en voorstelle vir die ontwerp en plasing van die dryfmiddel tenke is gemaak. Die gebruik van hitte pype as 'n alternatief vir elektriese verhittingselemente is ondersoek. Verskeie ontwerp aspekte word grafies voorgestel. Die bestuur van die vloeistof-dryfmiddel deur van oppervlak spannings apparaat gebruik te maak, is kwalitatief ondersoek. Voorstelle vir verdere navorsing in die veld van eenvoudige, lae-koste stuwer stelsels vir mikro-satelliete is gemaak. Meer spesifiek is hierdie voorstelle gerig op die termo-vloeidinamiese modellering van die dryfmiddel, verdere eksperimentele navorsing, tegnieke om klein stukragte te meet en vakuumtenk toetse.

<p>Food allergy is an IgE-mediated immunological disease, which affects almost 4% of the adult population and up to 6% of children. Proteins from milk, egg, peanuts, soybean, wheat, fish and nuts are the main cause of food allergies. A less common allergen is pea protein. The National Food Administration analyses undeclared pea protein and contaminations of pea protein in foods using rocket immunoelectrophoresis and immunodiffusion. For both methods an antiserum against pea protein is needed. The aim of this study has been to characterize a newly developed rabbit-antiserum against pea protein. It is important to know if the antiserum is specific against peas, the detection as well as the quantification limits before it can be taken into use. The results of the study show that the antiserum was not absolutely specific, since it cross-reacted with chickpeas, fenugreek and lenses. However there is an "in-house" established PCR-method that can distinguish between chickpeas, fenugreek and peas and that method can be used as a complement to the rocket immunoelectrophoresis. The PCR-method cannot be used alone because it is not quantitative. Rocket immunoelectro¬phoresis detects 0,003% pea protein with purified IgG-antibodies from the antiserum.</p>

This thesis explores how an Asteroid Sample Return Mission might make use of solar electric propulsion to send a spacecraft on a journey to the asteroid 1989ML and back. It examines different trajectories that can be used to get an asteroid sample return or similar spacecraft to an interplanetary destination and back in the most fuel-efficient manner. While current plans call for keeping such a spacecraft on the asteroid performing science experiments for approximately 90 days, it is prudent to inquire how lengthening or shortening this time period may affect mission fuel requirements. Using optimal control methods, various mission scenarios have been modeled and simulated. The results suggest that the amount of time that the spacecraft may spend on the asteroid surface can be approximated as a linear function of the available fuel mass. Furthermore, It can be shown that as maximum available thrust is decreased, the radial component of the optimal thrust vector becomes more pronounced.

Approved for public release, distribution is unlimited / This thesis explores using a direct pseudospectral method for the solution of optimal control problems with mixed dynamics. An easy to use MATLAB optimization package known as DIDO is used to obtain the solutions. The modeling of both low thrust interplanetary trajectories as well as aerocapture trajectories is detailed and the solutions for low thrust minimum time and minimum fuel trajectories are explored with particular emphasis on verification of the optimality of the obtained solution. Optimal aerocpature trajectories are solved for rotating atmospheres over a range of arrival Vinfinities. Solutions are obtained using various performance indexes including minimum fuel, minimum heat load, and minimum total aerocapture mass. Finally, the problem formulation and solutions for the mixed dynamic problem of low thrust trajectories with a terminal aerocapture maneuver is addressed yielding new trajectories maximizing the total scientific mass at arrival. / Lieutenant, United States Navy

Este trabalho objetivou determinar as modificações ambientais causadas pelo uso de filme de polietileno de baixa densidade (PEBD), em túneis baixos com perfurações de 0%, 5%, 10%, 15% e 20% no desempenho da cultura da rúcula (Eruca vesicaria sativa (Mill) Thell) durante o verão e o outono e da cultura do rabanete (Raphanus sativus L.) durante o inverno e a primavera. Como variáveis resposta analisaram-se a umidade relativa do ar, a temperatura ambiente, a temperatura do solo, a radiação solar, além das características morfológicas da cultura: a massa seca, a massa verde, número de folhas (altura, peso, largura da planta), além da produtividade por área em cada tratamento. Os resultados mostraram que as variáveis climáticas envolvidas não apresentaram resultados significativamente diferentes entre os diversos níveis de perfuração pesquisados (5%, 10%, 15% e 20%). No entanto, as alterações microclimáticas ocorridas pela influência das perfurações no filme plástico tornaram o microclima no interior dos túneis baixos propício ao melhor desenvolvimento da cultura da rúcula (Eruca vesicaria sativa (Mill)Thell), e do rabanete (Raphanus sativus L.), resultando em maior produtividade. / The purpose of this research was to determine the environmental changes that the low density polythylene with different perforated film area (5, 10, 15, 20%) may cause on the rocket press culture (Eruca vesicaria sativa (Mill) Thell) during summer and fall time and radish culture (Raphanus sativus L.) during winter and spring time in low tunnel conditions. The climate variables analyzed were the humidity and air temperature, soil temperature and solar radiation. The culture parameters used to compare the treatments were dry matter, green matter, morphologicals characteristics of the plants (number, height, width and weight of leaves) and productivity. The results showed that find any significative differences between the climate variables inside the low tunnel with different perforated film area (5, 10, 15, 20%). However, the modification caused by the low tunnel with perforated plastic did provide performance of rocket press culture (Eruca vesicaria sativa (Mill) Thell) development in summer and fall time, and radish culture (Raphanus sativus L.) development in winter and spring, had better productivity and marketable characteristics.

Propõe-se aqui uma metodologia de projeto aero-termo-estrutural de motores foguete a propelente sólido. O projeto de um motor foguete deve ser realizado com o objetivo de cumprir requisitos de uma missão. Para cada veículo espacial, com uma nova missão, um novo motor pode ser projetado, necessitando para isso de uma série de ferramentas robustas, capazes de compreender todas as combinações de esforços existentes no funcionamento de um motor, sob condições de altas pressões e temperaturas. A metodologia aqui proposta é testada e validada em bancada de ensaios desenvolvida para este fim. Os resultados obtidos mostram que a metodologia utilizada se aproxima bastante dos resultados teóricos e pode ser ajustada por coeficientes de eficiência com grande facilidade. / It is proposed here an aero-thermo-structural design methodology for solid propellant rocket motors. The design of a rocket motor must be carried out in order to fulfill requirements of a mission. For each new space vehicle, with a new mission, a new motor can be designed, requiring for it a variety of robust tools, able to comprise all combinations of load existing in the operation of a motor under high pressures and temperatures. The methodology proposed here is tested and validated in bank of tests developed for this purpose. The results show that the methodology is very close to the theoretical results and can be adjusted by coefficients of efficiency with great ease.

A degradação ambiental dos últimos anos tem motivado a preocupação a respeito da sustentabilidade das atividades humanas. O manejo inadequado da irrigação e adubação, e baixas precipitações, para lixiviar o excesso de sais aplicados via água de irrigação, podem acarretar a salinização dos solos. A hidroponia se constitui em uma alternativa, para a conservação do solo e preservação dos mananciais de água. A rúcula (Eruca sativa Mill) foi a cultura escolhida para este estudo, pois a sua produção vem se destacando entre as hortaliças. O presente trabalho teve por objetivo determinar a tolerância da rúcula à salinidade da solução nutritiva. O experimento foi conduzido em ambiente protegido localizado na área experimental do Setor de Hidráulica do Departamento de Engenharia Rural da Escola Superior de Agricultura Luiz de Queiroz - ESALQ/USP, no município de Piracicaba-SP. O delineamento experimental foi blocos ao acaso. Avaliaram-se nove níveis de salinidade obtidos com a adição de NaCl sendo estes 1,8; 3,5; 4,5; 5,5; 6,5; 7,5; 8,5; 9,5; 10,5 dS m-1. Os resultado obtidos demonstram que o aumento nos níveis de salinidade proporcionou redução em todos os parâmetros avaliados, exceto o número de folhas que não sofreu influência significativa e a relação raiz/parte aérea foi influenciada de forma crescente. A salinidade limiar encontrada foi de 2,57 dS m-1, com redução de 5,57% na produção para cada aumento unitário na salinidade. A cultura da rúcula foi classificada, como moderadamente sensível à salinidade. É possível obter produções satisfatórias utilizando águas salinas no cultivo hidropônico da rúcula. / The environmental degradation in recent years has motivated the concern about the sustainability of human activities. The inadequate management of irrigation and low rainfall fertilization, to leach the excess salts applied through irrigation water, can lead to soil salinization. Hydroponics constitutes an alternative to soil conservation and preservation of water sources. The rocket (Eruca sativa Mill) was the culture chosen for this study because its production has been increasing among the vegetables. This study aimed to determine the tolerance of the rocket to the salinity of the nutrient solution. The experiment was carried out in protected enviroment on the experimental area of the Hydraulics Section of the University of São Paulo (ESALQ/USP), Piracicaba, State of São Paulo, Brazil. The experimental design was randomized blocks. It were evaluated nine levels of salinity obtained with the addition of NaCl and these 1.8, 3.5, 4.5, 5.5, 6.5, 7.5, 8.5, 9.5, 10.5 dS m-1. The results obtained show that the increased levels of salinity caused a reduction in all parameters except the number of leaves was not affected and the ratio root/shoot was influenced incrementally. The salinity threshold was found to be 2.57 dS m-1, a reduction of 5.57% in production for each unit increase in salinity. The rocket press was classified as moderately sensitive to salinity. It is possible to obtain satisfactory production using saline water for hydroponic cultivation rocket press.