The Effect Of Jet Breakup Length On The Acoustic Coupling Of Like-Doublet Injectors, 2014 University of Alabama in Huntsville
The Effect Of Jet Breakup Length On The Acoustic Coupling Of Like-Doublet Injectors, Brian Sweeney
Von Braun Symposium Student Posters
No abstract provided.
Design Of A 3-D Printed Unified Hybrid Motor, 2014 University of Alabama in Huntsville
Design Of A 3-D Printed Unified Hybrid Motor, Matthew A. Hitt, Michael D. Mascaro
Von Braun Symposium Student Posters
No abstract provided.
Investigation Of Condensed And Early Stage Gas Phase Hypergolic Reactions, 2014 Purdue University
Investigation Of Condensed And Early Stage Gas Phase Hypergolic Reactions, Jacob Daniel Dennis
Open Access Dissertations
Traditional hypergolic propellant combinations, such as those used on the space shuttle orbital maneuvering system first flown in 1981, feature hydrazine based fuels and nitrogen tetroxide (NTO) based oxidizers. Despite the long history of hypergolic propellant implementation, the processes that govern hypergolic ignition are not well understood. In order to achieve ignition, condensed phase fuel and oxidizer must undergo simultaneous physical mixing and chemical reaction. This process generates heat, intermediate condensed phase species, and gas phase species, which then may continue to react and generate more heat until ignition is achieved. The process is not well understood because condensed and …
Investigation Of Pulse Detonation Engine Flow Conditions For Turbomachinery Integration, 2014 Embry-Riddle Aeronautical University - Daytona Beach
Investigation Of Pulse Detonation Engine Flow Conditions For Turbomachinery Integration, Luis Estefano Ferrer-Vidal Espa˜Na-Heredia
Doctoral Dissertations and Master's Theses
Pressure gain combustion has been known to be more thermodynamically efficient than its constant pressure counterpart, which employs deflagration. Integration of pressure gain combustors into gas turbine engines has been and still is one of the most important challenges facing the gas turbine industry. Pressure gain combustion devices are inherently unsteady. This unsteadiness affects turbomachinery components designed using steady operation assumptions, and results in mechanical inefficiencies which could outweigh the thermal efficiency benefits. Understanding of turbine components specifically made to operate in the exhaust conditions provided by a pressure gain combustor may yield new turbine design paradigms. As a first …
Multi-Stage Axial Compressor With Counter-Rotation Using Accessory Drive, 2014 Embry-Riddle Aeronautical University
Multi-Stage Axial Compressor With Counter-Rotation Using Accessory Drive, Vinod Gehlot, Magdy S. Attia
Publications
A multi-stage axial compressor for counter rotation. A first series of rotor blade assemblies are mounted on and rotate with the driveshaft, each rotor blade assembly of the first series comprising a rotating stage of the multi-stage axial compressor. A second series of rotor blade assemblies provide a counter-rotating stage of the multi-stage axial compressor. An accessory drive links the second series of rotor blade assemblies to the driveshaft and causes counter-rotation of the second series of rotor blade assemblies.
Microthruster Fabrication And Characterization: In Search Of The Optimal Nozzle Geometry For Microscale Rocket Engines, 2014 Purdue University
Microthruster Fabrication And Characterization: In Search Of The Optimal Nozzle Geometry For Microscale Rocket Engines, Katherine L. Fowee, Alina Alexeenko
The Summer Undergraduate Research Fellowship (SURF) Symposium
A major consideration in microsatellite design is the engineering of micropropulsion systems that can deliver the required thrust efficiently with tight restrictions on space, weight, and power. Cold gas thrusters are one solution to the demand for smaller propulsion systems to accommodate the advancements in technology that have allowed for a reduction in the size and thus the cost of satellites. While much research has been done in understanding the flow regimes within these microthrusters, there is a need to understand how different nozzle designs affect microthruster performance. This requires that experimental data be collected on varying nozzles shapes (orifices, …
Design And Fabrication Of A Low-Cost Turbine Engine Component Testbed (Tect), 2014 University of Tennessee - Knoxville
Design And Fabrication Of A Low-Cost Turbine Engine Component Testbed (Tect), Joshua A. Hartman
Masters Theses
With gas turbine engine testing becoming very expensive because of the increasing complexity involved with the engine, engine subsystems, and test support systems, a low-cost Turbine Engine Component Testbed (TECT) is proposed. This engine build is given the designation J1-H-02. In the present study, a small augmented gas turbine engine (GTE) is constructed. The TECT engine is built with modularity as a key design consideration to allow for flame-tube patterns and augmentor sections to be changed quickly for combustion experiments that have gained impetus due to combustion anomalies/instabilities inherent with future military engine augmentors. This testbed allows for an effective …
Hybrid Rocket Design Study Utilizing Nozzle Cooling And Aft-End Vortex Oxidizer Injection, 2014 University of Tennessee - Knoxville
Hybrid Rocket Design Study Utilizing Nozzle Cooling And Aft-End Vortex Oxidizer Injection, John Nicholas Quigley
Masters Theses
The current study focused on two innovations intended to reduce the cost and enhance the performance of hybrid rockets. The majority of the emphasis was placed on the design, fabrication and testing of a 3-D printed, water cooled nozzle. This work was done as proof of concept to show that complex, high temperature components could be manufactured using these new techniques, thereby substantially bringing down fabrication costs and allowing configurations that are not feasible using traditional machining. A water-cooled calorimeter nozzle was made and used in thrust stand tests to verify analytic and numerical heating models used in the design …
Characterization And Testing Of A 5.8 Kv Sic Pin Diode For Electric Space Propulsion Applications, 2014 University of Nebraska-Lincoln
Characterization And Testing Of A 5.8 Kv Sic Pin Diode For Electric Space Propulsion Applications, Alexandra Toftul
Department of Electrical and Computer Engineering: Dissertations, Theses, and Student Research
Inductive Pulsed Plasma Thrusters (IPPTs) are a type of in-space propulsion that has multiple advantages over conventional chemical propulsion for long-duration, deep space missions. Existing IPPT prototypes utilize spark gap switches, however these are subject to corrosion problems that make them unreliable for long-term use. Recent advances in solid state switching technology have opened up a variety of switching options that could provide greater reliability, controllability, and increased energy efficiency. Taking advantage of this, a novel thruster drive circuit topology containing a high-power silicon controlled rectifier (SCR) and series fast recovery diode (FRD) is proposed that is expected to increase …
Lightweight Uav Launcher, 2014 California Polytechnic State University - San Luis Obispo
Lightweight Uav Launcher, Ben Miller, Christian Valoria, Corinne Warnock, Jake Coutlee
Mechanical Engineering
This report discusses the design, construction, and testing of a lightweight, portable UAV launcher. There is a current need for a small team of soldiers to launch a US Marine Tier II UAV in a remote location without transport. Research was conducted into existing UAV launcher designs and the pros and cons of each were recorded. This research served as a basis for concept generation during the initial design development stage. It was required that the design weigh less than 110 lbs, occupy a smaller volume than 48" x 24" 18" in its collapsed state, be portable by a single …
Dual High-Voltage Power Supply For Use On Board A Cubesat, 2014 California Polytechnic State University, San Luis Obispo
Dual High-Voltage Power Supply For Use On Board A Cubesat, Nicholas Weiser
Master's Theses
Since their conception in 1999, CubeSats have come and gone a long way. The first few that went into space were more of a “proof of concept,” and were more focused on sending simple data and photographs back to Earth. Since then, vast improvements have been made by over 40 universities and private firms, and now CubeSats are beginning to look towards interplanetary travel. These small satellites could provide a cost effective means of exploring the galaxy, using off the shelf components and piggy-backing on other launch vehicles with more expensive payloads. However, CubeSats are traditionally launched into Low Earth …
Localization And System Identification Of A Quadcopter Uav, 2014 Western Michigan University
Localization And System Identification Of A Quadcopter Uav, Kenneth Befus
Masters Theses
The research conducted explores the comparison of several trilateration algorithms as they apply to the localization of a quadcopter micro air vehicle (MAV). A localization system is developed employing a network of combined ultrasonic/radio frequency sensors used to wirelessly provide range (distance) measurements defining the location of the quadcopter in 3-dimensional space. A Monte Carlo simulation is conducted using the extrinsic parameters of the localization system to evaluate the adequacy of each trilateration method as it applies to this specific quadcopter application. The optimal position calculation method is determined.
Furthermore, flight testing is performed in which real range measurement data …
The Effect Of The 2-Dimensional Magnetic Field Profile In Hall Thrusters, 2014 Embry-Riddle Aeronautical University - Daytona Beach
The Effect Of The 2-Dimensional Magnetic Field Profile In Hall Thrusters, Megan Lewis Harvey
Doctoral Dissertations and Master's Theses
Electric propulsion engines, in particular Hall thrusters, provide the possibility of long-distance, low-cost space travel. The geometrical details of the Hall thrusters, especially the magnetic field prole, are crucial to improving their efficiency. The effect of the magnetic field structure was investigated using a simple, two-dimensional model, assuming axial symmetry. The previous one-dimensional conclusion, namely that the details of the shape of the magnetic field are unimportant, was confirmed. This result has implications for the design of future Hall thruster engines, with an eye toward maximizing their efficiency.
Thermal Loss Determination For A Small Internal Combustion Engine, 2014 Air Force Institute of Technology
Thermal Loss Determination For A Small Internal Combustion Engine, Joshua A. Rittenhouse
Theses and Dissertations
Three analysis techniques were used to measure the heat rejection of a 55 cc air-cooled two-stroke engine. This study was performed as part of a larger effort aimed at extending range and endurance limitations of Group 1 & 2 Remotely Piloted Aircraft (RPA). The engine selected for the study was a 55 cc gasoline-fueled, carbureted, spark-ignition engine made by 3W-Modellmotoren and is representative of RPA engines in these groups. With a surface area to volume ratio of 1.48 1/cm, the engine is in a size region where thermal losses begin to dominate engine efficiency and thermal efficiencies …
The Use Of An Ultra-Compact Combustor As An Inter-Turbine Burner For Improved Engine Performance, 2014 Air Force Institute of Technology
The Use Of An Ultra-Compact Combustor As An Inter-Turbine Burner For Improved Engine Performance, Jose L. Miranda
Theses and Dissertations
An Inter-Turbine Burner (ITB) represents a novel mechanism for generating additional work from a gas turbine engine in applications where an afterburner would typically be used. An ITB can achieve higher thermal efficiencies over a typical afterburner while also generating shaft work versus only additional thrust. In an effort to investigate the potential applications for the ITB, a numerical engine cycle comparison was made between the ITB cycle and a conventional afterburning cycle using the Numerical Propulsion System Simulation (NPSS). In the case of thrust augmentation, the ITB model outperformed the afterburning model when Thrust Specific Fuel Consumption (TSFC) is …
The Development Of A Nanosatellite-Class Sunsat At The University Of North Dakota, 2014 SelectedWorks
The Development Of A Nanosatellite-Class Sunsat At The University Of North Dakota, Corey Bergsrud, Jeremy Straub, Robert Bernaciak, Subin Shahukhal, Benjamin Kading, Karl Williams, Hossein Salehfar, Johnathan Mcclure, James Casler, David Whalen, Elizabeth Becker, Sima Noghanian
Jeremy Straub
This poster presents the details of work on the SunSat spacecraft design initiative at the University of North Dakota. This project seeks to advance technologies1 and to increase public awareness of Space Solar Power based via visualization, science and engineering work. It will also focus on the development and demonstration of a workable solution and consider the economic benefits2 that the proposed (and alternate) solutions may generate. This poster details the design project which will construct a transmitting Nano Space Solar Power Satellite (NSSPS) and a power reception satellite for a space-to-space Microwave Wireless Power (MWP) demonstration. The SmallSatstyle spacecraft4, …
Could We Colonize Venus?, 2014 Minnesota State University, Mankato
Could We Colonize Venus?, Nihad E. Daidzic
Aviation Department Publications
No abstract provided.
Development Of Safety Standards For Cubesat Propulsion Systems, 2014 California Polytechnic State University, San Luis Obispo
Development Of Safety Standards For Cubesat Propulsion Systems, Liam Jon Cheney
Master's Theses
The CubeSat community has begun to develop and implement propulsion systems. This movement represents a new capability which may satisfy mission needs such as orbital and constellation maintenance, formation flight, de-orbit, and even interplanetary travel. With the freedom and capability granted by propulsion systems, CubeSat providers must accept new responsibilities in proportion to the potential hazards that propulsion systems may present.
The Cal Poly CubeSat program publishes and maintains the CubeSat Design Specification (CDS). They wish to help the CubeSat community to safety and responsibly expand its capabilities to include propulsive designs. For this reason, the author embarked on the …
Rocket Flight Path, 2014 University of South Florida
Rocket Flight Path, Jamie L. Waters
Jamie L Waters
This project uses Newton’s Second Law of Motion, Euler’s method, basic physics, and basic calculus to model the flight path of a rocket. From this project, one can find the height and velocity at any point from launch to the maximum altitude, apogee. Once complete this can be compared to what the actual values were to see if the method is a plausible way of estimation. The rocket used in this project is modeled after Bullistic-1 which was launched by the Society of Aeronautics and Rocketry at the University of South Florida.
Evolution Of Perturbations In Flow Field Mechanics, 2014 Boston University
Evolution Of Perturbations In Flow Field Mechanics, Samantha R. Bell, David Forliti, Nils Sedano, Kriss Vanderhyde
STAR Program Research Presentations
This project explores the stability analysis of a given flow field. Specifically, where the peak disturbance occurs in a flow as this is the disturbance that is most likely to occur. In rocket combustion, it is important to understand where the maximum disturbance occurs so that the mixing of fuel can be stabilized. The instabilities are the results of frequencies in the area surrounding the flow field. The linear stability governing equations are employed to better understand the disturbance. The governing equations for continuity and momentum in the x and y directions are used to form an equation for the …