Progress Towards An Opposed Piston Two Stroke Gasoline Aviation Engine, 2017 Southern Illinois University Carbondale
Progress Towards An Opposed Piston Two Stroke Gasoline Aviation Engine, Donald R. Morris
ASA Multidisciplinary Research Symposium
Opposed Piston Engine Technology is not new, but its application to small two-stroke gasoline engines is unexplored. This presentation explores the potential advantages of such an engine as well as progress towards a workable design.
Prediction Of Solid Oxide Fuel Cell Performance Using Artificial Neural Network, 2017 University of Texas at Tyler
Prediction Of Solid Oxide Fuel Cell Performance Using Artificial Neural Network, M. A. Rafe Biswas, Kamwana N. Mwara
M. A. Rafe Biswas
Blended Wing Body Propulsion System Design, 2017 Georgia Institute of Technology
Blended Wing Body Propulsion System Design, Parth Kumar, Adeel Khalid
International Journal of Aviation, Aeronautics, and Aerospace
This research paper focuses on the optimization of the propulsion system of a blended wing body design. Two different aspects of the design, the engine placement and count, and the engine itself, are investigated. The preliminary wing of the BWB is created through aerodynamic analysis, and is kept as a constant over the different propulsion system configurations. The engine parameters are first investigated. Equations are derived to express takeoff distance and climb rate as a function of engine sea level thrust, cruise thrust, and the number of engines. Nearly 150 different engine models, in BWB configurations of 2, 3, 4 ...
Additive Manufacturing Of High Solids Loading Hybrid Rocket Fuel Grains, 2017 Olivet Nazarene University
Additive Manufacturing Of High Solids Loading Hybrid Rocket Fuel Grains, Stephen P. Johnson, Michael Baier, Ibrahim E. Gunduz, Steven F. Son
The Summer Undergraduate Research Fellowship (SURF) Symposium
Hybrid rocket motors offer many of the benefits of both liquid and solid rocket systems. Like liquid engines, hybrid rocket motors are able to be throttled, can be stopped and restarted, and are safer than solid rocket motors since the fuel and oxidizer are in different physical states. Hybrid rocket motors are similar to solid motors in that they are relatively simple and have a high density-specific impulse. One of the major drawbacks of hybrid rocket motors is a slower burning rate than solid rocket motors. Complex port geometries provide greater burning surface area to compensate for lower burning rates ...
Operation Of The T-100 Hall Effect Thruster, 2017 Purdue University
Operation Of The T-100 Hall Effect Thruster, Glynn Smith, Omar Dary, Alexey Shashurin
The Summer Undergraduate Research Fellowship (SURF) Symposium
The introduction of Hall Effect Thrusters from the former Soviet Union to the United States generated considerable interest in using the propulsion system aboard Western spacecraft. The established programs evaluated the SPT-100, and TAL-55 Hall Effect Thrusters for efficiency, lifetime, and performance characteristics. The T-100 model garnered only minor interest during this time compared with the same generation counterparts, the SPT-100, and TAL-55. This gap in knowledge on the efficiency, and performance of the T-100 warrants investigation into the design, and operation of the thruster. Operational characteristics will be measured on a restored T-100 Hall Thruster, using argon as a ...
Jfs Turbine Engine For Cal Poly Mechanical Engineering Department, 2017 California Polytechnic State University, San Luis Obispo
Jfs Turbine Engine For Cal Poly Mechanical Engineering Department, Dorian Capps, Zoe Kai Tuggle
This project concerns the development of a gas turbine engine laboratory activity for use in one of Cal Poly’s technical elective courses in the Mechanical Engineering Department, ME 444: Combustion Engine Design. The class is taught by Dr. Patrick Lemieux, who is also in charge of the on-campus engines lab where the turbine engine will be installed. The engine itself is a JFS-100-13A turboshaft engine that will be coupled to an electric dynamometer inside of the dyno test cell. Students taking the ME 444 class, likely starting in Winter Quarter of 2018, will be able to perform hands-on experiments ...
Actuator Disk Theory For Compressible Flow, 2017 California Polytechnic State University, San Luis Obispo
Actuator Disk Theory For Compressible Flow, Htet Htet Nwe Oo
Master's Theses and Project Reports
Because compressibility effects arise in real applications of propellers and turbines, the Actuator Disk Theory or Froude’s Momentum Theory was established for compressible, subsonic flow using the three laws of conservation and isentropic thermodynamics. The compressible Actuator Disk Theory was established for the unducted (bare) and ducted cases in which the disk was treated as the only assembly within the flow stream in the bare case and enclosed by a duct having a constant cross-sectional area equal to the disk area in the ducted case. The primary motivation of the current thesis was to predict the ideal performance of ...
An Investigation Into The Potential Benefits Of Distributed Electric Propulsion On Small Uavs At Low Reynolds Numbers, 2017 Old Dominion University
An Investigation Into The Potential Benefits Of Distributed Electric Propulsion On Small Uavs At Low Reynolds Numbers, Engin Baris
Mechanical & Aerospace Engineering Theses & Dissertations
Distributed electric propulsion systems benefit from the inherent scale independence of electric propulsion. This property allows the designer to place multiple small electric motors along the wing of an aircraft instead of using a single or several internal combustion motors with gear boxes or other power train components. Aircraft operating at low Reynolds numbers are ideal candidates for benefiting from increased local flow velocities as provided by distributed propulsion systems.
In this study, a distributed electric propulsion system made up of eight motor/propellers was integrated into the leading edge of a small fixed wing-body model to investigate the expected ...
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.
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 ...
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 ...
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.
The Scaling Of Loss Pathways And Heat Transfer In Small Scale Internal Combustion Engines, 2016 Air Force Institute of Technology
The Scaling Of Loss Pathways And Heat Transfer In Small Scale Internal Combustion Engines, Joseph K. Ausserer
Theses and Dissertations
Prior literature indicates fuel conversion efficiency and normalized power deteriorate increasingly rapidly with decreasing displacement, but does not fully reveal the driving losses. The literature also suggested that increasing losses relax the required fuel anti-knock index (AKI), but offered conflicting conclusions on the performance impact. This comprehensive experimental study of three, 28 cm3 to 85 cm3 displacement, commercial-off-the-shelf (COTS), two-stroke ICEs identified short-circuiting as having the most deleterious impact on COTS engine performance in this size range. Heat transfer losses were comparable to larger engines for displaced volumes greater than 10 cm3. An engine friction model was developed that uses ...
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 ...