In-House Fabrication Of Temperature Sensitive Paint For Turbine Cooling Research, 2017 Embry-Riddle Aeronautical University
In-House Fabrication Of Temperature Sensitive Paint For Turbine Cooling Research, Mayur D. Patel, Mark A. Ricklick
Beyond: Undergraduate Research Journal
The Temperature Sensitive Paint (TSP) is a widely used method in measuring and visualizing flow separation and heat transfer. Compared to the cost and time consumption needed for methods such as pitot tubes, temperature sensitive paint is a cheaper alternative. Due to high usage in College of Engineering research projects, it was determined that in house fabrication of temperature sensitive paint would reduce time and cost limitations. For initial stages, literature research was performed to determine the recipe of intensity based TSP with luminophore and polymer binder that operated optimum at temperatures from 0-100°C. Europium III thenoyltrifluoroacetonate was determined ...
Lehmier Launch System, 2017 The University of Akron
Lehmier Launch System, Dylan Lehmier 5248813
Honors Research Projects
The Lehmier Launch System was designed to propel a 120lb rocket 30,000 feet. Creating 2150 psi of thrust and 27,500 N-s of total impulse, it is the largest rocket motor ever used by the Akronauts Rocket Design Team.
Enhancement Of Volumetric Specific Impulse In Htpb/Ammonium Nitrate Mixed Hybrid Rocket Systems, 2016 Utah State University
Enhancement Of Volumetric Specific Impulse In Htpb/Ammonium Nitrate Mixed Hybrid Rocket Systems, Jacob Ward Forsyth
All Graduate Plan B and other Reports
Hybrid rocket systems are safer and have higher specific impulse than solid rockets. However, due to large oxidizer tanks and low regression rates, hybrid rockets have low volumetric efficiency and very long longitudinal profiles, which limit many of the applications for which hybrids can be used. This research investigates a method for increasing the volumetric efficiency and improving the form factor of hybrid rocket systems by a non-combustible load of solid oxidizer to the hybrid fuel grain. Including such oxidizers increases the regression rate of the fuel and lowers the amount of fluid oxidizer needed for optimal combustion. This type ...
Combustion Tap-Off Cycle, 2016 Embry-Riddle Aeronautical University
Combustion Tap-Off Cycle, Nicole Shriver
College of Engineering
This directed study was done on the combustion tap-off cycle, which is a unique type of rocket engine cycle. The combustion tap-off cycle is not one that is mentioned or discussed in the AE 414 Space Propulsion class. This cycle has only been used by two engines, the J-2S and BE-3. The J-2S was created in the 1960’s by heritage Rocketdyne. This engine has never been flown, but it has been tested extensively. This engine proved that the tap-off cycle was possible for rockets and useful for its throttling capabilities. The BE-3 was developed by Blue Origin for use ...
Fundamental Studies Of Electrochemical Reactions And Microfluidics In Proton Exchange Membrane Electrolyzer Cells, 2016 University of Tennessee, Knoxville
Fundamental Studies Of Electrochemical Reactions And Microfluidics In Proton Exchange Membrane Electrolyzer Cells, Jingke Mo
In electrochemical energy devices, including fuel cells, electrolyzers and batteries, the electrochemical reactions occur only on triple phase boundaries (TPBs). The boundaries provide the conductors for electros and protons, the catalysts for electrochemical reactions and the effective pathways for transport of reactants and products. The interfaces have a critical impact on the overall performance and cost of the devices in which they are incorporated, and therefore could be a key feature to optimize in order to turn a prototype into a commercially viable product. For electrolysis of water, proton exchange membrane electrolyzer cells (PEMECs) have several advantages compared to other ...
Dji S-1000 Spreading Wings Octocopter: Determination Of Rotor Downwash Slipstream Size, 2016 University of Tennessee, Knoxville
Dji S-1000 Spreading Wings Octocopter: Determination Of Rotor Downwash Slipstream Size, Jonathan Lemieux
The DJI S-1000 Spreading Wings octocopter rotor downwash slipstream area of influence was measured in axial climb conditions and in straight level flight. These data were gathered using a simple apparatus of distributed anemometers and a custom made boom affixed to the drone. Straight level flight tests incurred autopilot oscillations that rendered the data gathering and analysis challenging. The best quality data was acquired during the axial climb flight tests. The axial climbs were conducted in calm winds. It was determined that the axial climbs under these conditions displaced the rotor slipstream 9 ± 2.5 cm to the rear of ...
Senior Design - Hybrid Rocket Conceptual Design, 2016 Selected Works
Senior Design - Hybrid Rocket Conceptual Design, Hardeo Chin
Assessment Of High Cycle Fatigue Crack Growth Under Different Stages Based On Crystal Plasticity Modeling, 2016 Beihang University; Collaborative Innovation Center of Advanced Aero-engine
Assessment Of High Cycle Fatigue Crack Growth Under Different Stages Based On Crystal Plasticity Modeling, Duoqi Shi, Shiwei Han, Xiaoguang Yang
The 8th International Conference on Physical and Numerical Simulation of Materials Processing
No abstract provided.
Anisoplanatic Electromagnetic Image Propagation Through Narrow Or Extended Phase Turbulence Using Altitude-Dependent Structure Parameter, Monish Ranjan Chatterjee, Ali Mohamed
Electrical and Computer Engineering Faculty Publications
The effects of turbulence on anisoplanatic imaging are often modeled through the use of a sequence of phase screens distributed along the optical path. We implement the split-step wave algorithm to examine turbulence-corrupted images.
Numerical Investigations Of A High Frequency Pulsed Gaseous Fuel Jet Injection Into A Supersonic Crossflow, 2016 University of Tennessee, Knoxville
Numerical Investigations Of A High Frequency Pulsed Gaseous Fuel Jet Injection Into A Supersonic Crossflow, Nehemiah Joel Williams
The investigation of fuel delivery mechanisms is a critical design point in the development of supersonic combustion ramjet (scramjet) technology. Primary challenges include proper penetration of the jet in the supersonic cross-flow while keeping total pressure losses and wall drag to a minimum. To reduce drag and heat loads especially at high burner entry Mach numbers it is desirable to use a minimally intrusive means of fuel delivery.
Pulsation of gaseous jets has been shown to increase penetration and mixing in subsonic flows. A limited number of experimental studies and even fewer numerical studies have suggested that when applied to ...
Estimation Of Performance Airspeeds For High-Bypass Turbofans Equipped Transport-Category Airplanes, 2016 AAR Aerospace Consulting, LLC
Estimation Of Performance Airspeeds For High-Bypass Turbofans Equipped Transport-Category Airplanes, Nihad E. Daidzic
Journal of Aviation Technology and Engineering
Conventional Mach-independent subsonic drag polar does not replicate the real airplane drag characteristics exactly and especially not in the drag-divergence region due to shock-induced transonic wave drag. High-bypass turbofan thrust is a complicated function of many parameters that eludes accurate predictions for the entire operating envelope and must be experimentally verified. Fuel laws are also complicated functions of many parameters which make optimization and economic analysis difficult and uncertain in the conceptual design phase. Nevertheless, mathematical models and predictions have its important place in aircraft development, design, and optimization. In this work, airspeed-dependent turbofan thrust and the new fuel-law model ...
Evaluation Of The Transmission Of Space Solar Power To Uavs By Microwave Transmission, Alexander Holland, Wilson Lysford, Jens Pearson, Jeremy Straub
Time-Of-Flight Based Sonic Speed Measurements For Cold Gas Thruster Development, 2016 University of Arkansas, Fayetteville
Time-Of-Flight Based Sonic Speed Measurements For Cold Gas Thruster Development, Brandon W. Kempf
Mechanical Engineering Undergraduate Honors Theses
The purpose of this thesis is to explore an experiment developed for validating the usage of a gaseous solution of water and propylene glycol for cold gas propulsion. The experiment involves a “Time of Flight” method of calculating the speed of sound in the gas and the corresponding specific heat ratio using a copper tube, two MEMS microphones, a piezoelectric speaker, and data-acquisition hardware. The experiment was calibrated using the known thermodynamic properties of air. The accuracy of the experiment was found to be within 0.6% for calculations of the speed of sound in air and within 1.0 ...
Computational Investigation Of Impingement Cooling For Regeneratively Cooled Rocket Nozzles, 2016 Embry-Riddle Aeronautical University
Computational Investigation Of Impingement Cooling For Regeneratively Cooled Rocket Nozzles, Bianca A. De Angelo
Dissertations and Theses
Jet impingement cooling is an internal cooling configuration used in the thermal management of temperature sensitive systems. With rocket engine combustion temperatures rising as high as 3600 K, it is essential for a cooling method to be applied to ensure that the nozzle integrity can be maintained. Therefore, a novel heat transfer study is conducted to investigate if jet impingement cooling is feasible for a regenerative cooling rocket nozzle application. Regenerative cooling for liquid propellant rockets has been widely studied. However, to the best of the author’s knowledge, there is currently no literature describing this method in conjunction with ...
Control System Requirements For A Nuclear Thermal Propulsion System, 2016 University of Tennessee, Knoxville
Control System Requirements For A Nuclear Thermal Propulsion System, Adam Hasse, Michael Smith, Bradley Pershke, Andrew Adams, Stephen GilliAm
University of Tennessee Honors Thesis Projects
No abstract provided.
Consideration Of Microwave Power Receiving By Uas Systems, 2016 Selected Works
Consideration Of Microwave Power Receiving By Uas Systems, Wilson Lysford, Alexander Holland, Jens Pearson, Jeremy Straub, Scott Kerlin
Early Afternoon Concurrent Panel Sessions: Commercial Space Industry Snapshot: Presentation: Small Catapult-Assisted Horizontal-Launch Reusable Rbcc Ssto Spaceplane For Economical Short-Duration Leo Access, 2016 AAR Aerospace Consulting, LLC
Early Afternoon Concurrent Panel Sessions: Commercial Space Industry Snapshot: Presentation: Small Catapult-Assisted Horizontal-Launch Reusable Rbcc Ssto Spaceplane For Economical Short-Duration Leo Access, Nihad E. Daidzic,
Aviation / Aeronautics / Aerospace International Research Conference
This article discusses the conceptual design, flight trajectory calculations, and utilization of the possible future horizontally-launched reusable Single-Stage-to-Orbit (SSTO) spaceplane for small payload short-duration manned/unmanned access to Low-Earth-Orbit (LEO). The 10,000 lb spaceplane would use 5,000 ft catapult-assist horizontal-launch facility and conduct powered approach and landing on conventional horizontal paved runways following the gliding atmospheric re-entry. To increase the economy of operation, the launch facility located at high elevations (4,000+ ft) equatorial region is required, such as, the plateaus in Kenya and Tanzania in Africa and/or Ecuador in South America. A 500-lb payload, including pilot-commander ...
Rocket Fin Test Fixture Development & Exploration Of Rotation Inducing Fin Design, 2016 The University of Akron
Rocket Fin Test Fixture Development & Exploration Of Rotation Inducing Fin Design, Ryan A. Saylor Mr., David J. Royak Mr., Jacob P. Byron Mr.
Honors Research Projects
The purpose of this senior project was to develop a method of applying rotation inducing rocket fin concepts to rockets for the benefit of the University of Akron Akronauts; the student led rocket design team. The project was performed independently of the team’s current efforts as a research and development endeavor for future team projects. Main project goals were divided into three parts: design a fin test fixture for verification testing in the University’s wind tunnel, develop a parameter-driven software model that could be used to generate design options with theoretical performance data as an output, and run ...
Divergent Plume Reduction Of A High-Efficiency Multistage Plasma Thruster, 2015 California Polytechnic State University - San Luis Obispo
Divergent Plume Reduction Of A High-Efficiency Multistage Plasma Thruster, Christopher M. Barlog
Master's Theses and Project Reports
High Efficiency Multistage Plasma Thrusters (HEMPTs) are a relatively new form of electric propulsion that show promise for use on a variety of missions and have several advantages over their older EP competitors. One such advantage is their long predicted lifetime and minimal wall erosion due to a unique periodic permanent magnet system. A laboratory HEMPT was built and donated by JPL for testing at Cal Poly. Previous work was done to characterize the performance of this thruster and it was found to exhibit a large plume divergence, resulting in decreased thrust and specific impulse. This thesis explores the design ...
Comment On Faa Rule Revision - Transport Category Aircraft, 2015 Embry Riddle Aeronautical University - Daytona Beach
Comment On Faa Rule Revision - Transport Category Aircraft, Paul F. Eschenfelder, Valter Battistoni
Paul F. Eschenfelder
No abstract provided.