Matching Items (763)
Filtering by
- All Subjects: Electrical Engineering
- All Subjects: Materials Science
- All Subjects: Aerospace Engineering
- Genre: Masters Thesis
Description
ABSTRACT As the technology length shrinks down, achieving higher gain is becoming very difficult in deep sub-micron technologies. As the supply voltages drop, cascodes are very difficult to implement and cascade amplifiers are needed to achieve sufficient gain with required output swing. This sets the fundamental limit on the SNR and hence the maximum resolution that can be achieved by ADC. With the RSD algorithm and the range overlap, the sub ADC can tolerate large comparator offsets leaving the linearity and accuracy requirement for the DAC and residue gain stage. Typically, the multiplying DAC requires high gain wide bandwidth op-amp and the design of this high gain op-amp becomes challenging in the deep submicron technologies. This work presents `A 12 bit 25MSPS 1.2V pipelined ADC using split CLS technique' in IBM 130nm 8HP process using only CMOS devices for the application of Large Hadron Collider (LHC). CLS technique relaxes the gain requirement of op-amp and improves the signal-to-noise ratio without increase in power or input sampling capacitor with rail-to-rail swing. An op-amp sharing technique has been incorporated with split CLS technique which decreases the number of op-amps and hence the power further. Entire pipelined converter has been implemented as six 2.5 bit RSD stages and hence decreases the latency associated with the pipelined architecture - one of the main requirements for LHC along with the power requirement. Two different OTAs have been designed to use in the split-CLS technique. Bootstrap switches and pass gate switches are used in the circuit along with a low power dynamic kick-back compensated comparator.
ContributorsSwaminathan, Visu Vaithiyanathan (Author) / Barnaby, Hugh (Thesis advisor) / Bakkaloglu, Bertan (Committee member) / Christen, Jennifer Blain (Committee member) / Arizona State University (Publisher)
Created2012
Description
This work uses Arizona State University’s (ASU) newly developed high-speed vehicle stability and control screening methodologies to reverse-engineer famous United States Air Force (USAF) flight tests from the 1950s and 1960s. This thesis analyzes the root cause of Chuck Yeager's fateful 1953 supersonic spin in the Bell X-1A to become the "Fastest Man Alive". This thesis then takes a look back at Neil Armstrong's inadvertent atmospheric skip in the North American X-15 and his subsequent hypersonic flight months later. The fundamental flying qualities assessment shown in this work begins with calculating rigid-body frequencies and damping ratios of an aircraft to Military Standard (MIL) requirements, and uses these to create a full, classical stability and control analysis of a high-speed vehicle. Through reverse engineering the flight envelopes and missions for the above aircraft, it appears that the near-disasters of each flight were due to a confluence of then overlooked, yet fundamental, aerodynamic instabilities.
ContributorsLorenzo, Will (Author) / Takahashi, Timothy T (Thesis advisor) / Dahm, Werner J.A. (Committee member) / Grandhi, Ramana V (Committee member) / Arizona State University (Publisher)
Created2023
Description
Machine learning advancements have led to increasingly complex algorithms, resulting in significant energy consumption due to heightened memory-transfer requirements and inefficient vector matrix multiplication (VMM). To address this issue, many have proposed ReRAM analog in-memory computing (AIMC) as a solution. AIMC enhances the time-energy efficiency of VMM operations beyond conventional VMM digital hardware, such as a tensor processing unit (TPU), while substantially reducing memory-transfer demands through in-memory computing. As AIMC gains prominence as a solution, it becomes crucial to optimize ReRAM and analog crossbar architecture characteristics. This thesis introduces an application-specific integrated circuit (ASIC) tailored forcharacterizing ReRAM within a crossbar array architecture and discusses the interfacing techniques employed. It discusses ReRAM forming and programming techniques and showcases chip’s ability to utilize the write-verify programming method to write image pixels on a conductance heat map. Additionally, this thesis assesses the ASIC’s capability to characterize different aspects of ReRAM, including drift and noise characteristics. The research employs the chip to extract ReRAM data and models it within a crossbar array simulator, enabling its application in the classification of the CIFAR-10 dataset.
ContributorsShort, Jesse (Author) / Marinella, Matthew (Thesis advisor) / Barnaby, Hugh (Committee member) / Sanchez Esqueda, Ivan (Committee member) / Arizona State University (Publisher)
Created2023
Description
Formula 1 car front wings have evolved significantly over the last fifty years. Looking back at the past decade shows significant changes made due to rules and regulations by the Federation Internationale de l'Automobile and an increased understanding of aerodynamic concepts. There seems to be a trend where aerodynamic design concepts, previously seen in aviation, are being applied to Formula 1 front wings; this helps race teams increase downforce and reduce drag. This thesis analyzes these changes made over the past years and relates the material back to material that was learned by the aviation industry and attempts to synthesize conceptual Formula 1 front Wing designs using VORLAX, a vortex lattice panel method, used in the aviation industry. This insight would be beneficial for Formula 1 teams as there are budget and time restrictions applied to Computational Fluid Dynamic and wind tunnel testing, but panel methods are run in a matter of seconds as opposed to hours or days. So, if verified, preliminary designs can be rapidly tested to optimize the workflow and reduce the time required for Computational Fluid Dynamic and wind tunnel testing.
ContributorsRatnayake, Sajana Sathsara (Author) / Takahashi, Timothy T (Thesis advisor) / Perez, Ruben E (Committee member) / Kim, Jeonglae (Committee member) / Arizona State University (Publisher)
Created2023
Description
This work presents two balanced power amplifier (PA) architectures, one at X-band and the other at K-band. The presented balanced PAs are designed for use in small satellite and cube satellite applications.The presented X-band PA employs wideband hybrid couplers to split input power to two commercial off-the-shelf (COTS) Gallium Nitride (GaN) monolithic microwave integrated circuit (MMIC) PAs and combine their output powers. The presented X-band balanced PA manufactured on a Rogers 4003C substrate yields increased small signal gain and saturated output power under continuous wave (CW) operation compared to the single MMIC PA used in the design under pulsed operation. The presented PA operates from 7.5 GHz to 11.5 GHz, has a maximum small signal gain of 36.3 dB, a maximum saturated power out of 40.0 dBm, and a maximum power added efficiency (PAE) of 38%.
Both a Wilkinson and a Gysel splitter and combiner are designed for use at K-band and their performance is compared. The presented K-band balanced PA uses Gysel power dividers and combiners with a GaN MMIC PA that is soon to be released in production.
ContributorsPearson, Katherine Elizabeth (Author) / Kitchen, Jennifer (Thesis advisor) / Bakkaloglu, Bertan (Committee member) / Ozev, Sule (Committee member) / Arizona State University (Publisher)
Created2023
Description
This thesis presents a study of Boron Nitride (BN) and Copper (Cu)/BN multilayer thin films in terms of synthesis, chemical, structural, morphological, and mechanical properties characterization.
In this study, the influence of Ar/N₂ flow rate in synthesizing stoichiometric BN thin films via magnetron sputtering was investigated initially. Post magnetron sputtering, the crystalline nature and B:N stoichiometric ratio of deposited thin films were investigated by X-ray diffraction (XRD) and X-ray Photoelectron Spectroscopy (XPS) respectively. Thicknesses revealed by ellipsometry analysis for nearly stoichiometric B:N thin films and their corresponding deposition times were used for estimating BN interlayer deposition times during the deposition of Cu/BN multilayer thin films. To characterize the microstructure of the synthesized Cu/BN multilayer thin films, XRD and scanning electron microscopy (SEM) have been used. Finally, a comparison of nanoindentation measurements on pure Cu and Cu/BN multilayer thin films having different number of BN interlayers were used for studying the influence of BN interlayers on improving mechanical properties such as hardness and elastic modulus.
The results show that the stoichiometry of BN thin films is dependent on the Ar/N₂ flow rate during magnetron sputtering. An optimal Ar/N₂ flow rate of 13:5 during deposition was required to achieve an approximately 1:1 B:N stoichiometry. Grazing incidence and powder XRD analysis on these stoichiometric BN thin films deposited at room temperature did not reveal a phase match when compared to hexagonal boron nitride (h-BN) and cubic boron nitride (c-BN) reference XRD patterns. For a BN thin film deposition time of 5 hours, a thickness of approximately 40 nm was achieved, as revealed by ellipsometry. XRD and microstructure analysis using scanning electron microscopy (SEM) on pure Cu and Cu/BN thin films showed that the Cu grain size in Cu/BN thin films is much finer than pure Cu thin films. Interestingly, nanoindentation measurements on pure Cu and Cu/BN thin films having a similar overall thickness demonstrated that hardness and Young’s modulus of the films were improved significantly when BN interlayers are present.
ContributorsCaner, Sumeyye (Author) / Rajagopalan, Jagannathan (Thesis advisor) / Oswald, Jay (Committee member) / Solanki, Kiran (Committee member) / Arizona State University (Publisher)
Created2023
Description
This thesis addresses the issue of assessing longitudinal and lateral-directional trim capability during the conceptual design process. Modern high-performance aircraft are likely to feature complex flight control systems where the control system may independently command every control surface to develop necessary moments. However, to prove stability and controllability on such an aircraft requires a near-final set of control laws. This requirement is onerous at the conceptual design level, where engineering methods need to facilitate rapid, multidisciplinary design optimization trades. This work considers the differences in Attainable Moment Sets across a wide variety of airframes using a simplified “pre-mix” approach to controls as well as a model where the control systems have independent command authority over each control surface. This work indicates that the “independent-single-panel” model offers modest improvements in attainable moments over a “pre-mix” strategy. This suggests that a “pre-mix” approach used to assess basic combined trim problems will not lead to an overly conservative final design.
ContributorsHeinz, Joshua Holden (Author) / Takahashi, Timothy (Thesis advisor) / Dahm, Werner (Committee member) / Cotting, M. Christopher (Committee member) / Arizona State University (Publisher)
Created2023
Description
Digital signal processing accelerator architectures are designed to provide either high-energy efficiency or high programmability depending on the targeted application and use case. For example, Domain Adaptive Processor (DAP), a highly reconfigurable array architecture, designed by University of Michigan, for signal processing workloads is highly energy efficient but difficult to program. DAP consists of 8x8 array of Processing elements (PE) with each PE containing four heterogeneous SUB-PEs. Each SUB-PE has its own instruction memory and is capable of executing Very Large Instruction Word (VLIW) instructions. Unfortunately, instructions have to be written for every cycle of computation for each SUB-PE used in the application and handcrafted such that all the inter-PE dependencies are synchronized. This thesis builds up on prior work at Arizona State University(ASU) to make DAP more programmable. First, the compiler back-end developed at ASU is extended with more features. Prior work introduced DAP Instruction Set Architecture (ISA), an assembly instruction format, and proposed a compiler framework, called DAP Assembler, with optimization passes to reduce the complexity of programming applications in DAP. While this back-end infrastructure helped generated code with relative ease compared to Very Large Instruction Word (VLIW) code by hand, the output of the code generated was not software-pipelined and the code generated for each Processing Element(PE) had to be manually synchronized. So in this thesis, DAP Assembler tool is extended to support software-pipelining for high throughput applications. Further, a generic synchronization tool is proposed to synchronize instructions in a multi-PE setup and integrated with DAP Assembler to generate synchronized high-throughput application code. Second, a Multi-Level Intermediate Representation(MLIR) based compiler front-end infrastructure is proposed to first lower the application code written by the programmer to an Intermediate Representation (IR) that is suitable for generic array architectures and then further converted to DAP-specific IR that can be used for generating machine code for DAP using DAP ISA. This two stage process enables this infrastructure to be more easily adapted to other array architectures. The first conversion pass uses a designer-provided modular hardware architecture information, called Resource Registry, to allocate operations in the input IR to resources in the Resource registry and capture all data movement. While the resource registry changes from architecture to architecture, the conversion pass algorithm is generic and can be used for other architectures. The second conversion pass is more geared towards DAP and integrates DAP specific constructs to generate optimized instruction in DAP ISA. Multiple kernels such as matrix multiplication, vector-vector addition were implemented using this infrastructure and the code generated by the tool verified to be functionally correct.
ContributorsMurugan, Narayanan (Author) / Chakrabarti, Chaitali Dr (Thesis advisor) / Akoglu, Ali Dr (Committee member) / Bliss, Daniel Dr (Committee member) / Arizona State University (Publisher)
Created2023
Description
The objective of this study is to understand how to integrate conical spike external compression inlets with high bypass turbofan engines for application on future supersonic airliners. Many performance problems arise when inlets are matched with engines as inlets come with a plethora of limitations and losses that greatly affect an engine’s ability to operate. These limitations and losses include drag due to inlet spillage, bleed ducts, and bypass doors, as well as the maximum and minimum values of mass flow ratio at each Mach number that define when an engine can no longer function. A collection of tools was developed that allow one to calculate the raw propulsion data of an engine, match the propulsion data with an inlet, calculate the aerodynamic data of an aircraft, and combine the propulsion and aerodynamic data to calculate the installed performance of the entire propulsion system. Several trade studies were performed that tested how changing specific design parameters of the engine affected propulsion performance. These engine trade studies proved that high bypass turbofan engines could be developed with external compression inlets and retain effective supersonic performance. Several engines of efficient fuel consumption and differing bypass ratios were developed through the engine trade studies and used with the aerodynamic data of the Concorde to test the aircraft performance of a supersonic airliner using these engines. It was found that none of the engines that were tested came close to matching the supersonic performance that the Concorde could achieve with its own turbojet engines. It is possible to speculate from the results several different reasons why these turbofan engines were unable to function effectively with the Concorde. These speculations show that more tests and trade studies need to be performed in order to determine if high bypass turbofan engines can be developed for effective usage with supersonic airliners in any possible way.
ContributorsCleary, Spencer (Author) / Takahashi, Timothy (Thesis advisor) / White, Daniel (Committee member) / Dahm, Werner (Committee member) / Arizona State University (Publisher)
Created2018
Description
Kuwait is committed to implementing the Kyoto Protocol in “Vision 2035” to reduce greenhouse gas emissions by shifting to the use of wind and solar energies [1]. The specific goal of the Vision 2035 is for renewables to comprise 15% of Kuwait’s electrical generation by 2030. Wind and solar are abundant in Kuwait and can easily provide 15% of the total electrical generation. However, there are three significant obstacles. The first is Kuwait currently depends heavily on rapidly diminishing fossil fuels which are the major sources of CO2, NOx, and SOx emissions. Unfortunately, current plans are to build two conventional power stations by 2024. The purpose is to cover the energy needs for growing population. The second problem is that Kuwait has a very small land area. Consequently, there is limited space to build new utility-scale renewable power stations. The third issue is the low electricity tariff provides little incentive for the population to save energy. Offshore wind farms have the potential to provide thousands of GWh/yr to accomplish the goals of Vision 2035. Kuwait has a vast untapped supply of offshore wind energy. Specifically, there are eight offshore locations in which 50 turbines could be built each, for a total of 400 turbines. Using 4.2 MW turbines, this would provide 1.68 GW of wind energy, and increase the renewable portion of the electrical energy production to 13.93% (including Shagaya renewable park). Installing battery storage with the proposed wind turbines could provide fast ramp response which would serve to complement existing power production on Kuwait’s grid. In this work, six different turbines with different sizes are considered from 2.5 MW to 4.2 MW (from well-known manufacturers, such as, Nordex and Vestas), but ultimately 4.2 MW turbines are recommended. Data for this study has been supplied by: A) Civil Aviation -- temperature and wind speed, B) Ministry of Electricity and Water (MEW) -- electricity data, and C) Public Authority for Civil Information -- population data.
ContributorsAlotaibi, Abdullah Saqer (Author) / Calhoun, Ronald (Thesis advisor) / Kitchen, Jennifer (Thesis advisor) / Roedel, Ronald (Committee member) / Mayyas, Abdul Ra'ouf (Committee member) / Arizona State University (Publisher)
Created2020