Computational Fluid Dynamics Is Key To Better Flying Aircraft,
2016
Minnesota State University, Mankato
Computational Fluid Dynamics Is Key To Better Flying Aircraft, Nihad E. Daidzic
Aviation Department Publications
No abstract provided.
Configuration Validation Of A Novel In-Space Propellant Storage And Transfer System,
2016
Embry-Riddle Aeronautical University
Configuration Validation Of A Novel In-Space Propellant Storage And Transfer System, Priyadarshan Sundararaju
Doctoral Dissertations and Master's Theses
The concept of developing a new technology for on-orbit storage and refueling system has been a great interest among scientists for many decades. This study is about Centaur-based on-orbit propellant storage and transfer. This system takes the advantage of rotational settling to a simple fluid management (FM) system. Specifically, enabling settled fluid transfer and settled pressure control between two tanks. This thesis work focuses on configuration and validation of static and dynamic stability, mass gauging and CFD analysis of the rotational propellant transfer method in space. The application of this technology in Low Earth Orbit (LEO) and Geo-Synchronous Orbit (GEO) …
2016 Summer-Fall Graduate Recognition Program,
2016
The University of Alabama in Huntsville
2016 Summer-Fall Graduate Recognition Program, Propulsion Research Center, Robert Frederick
PRC Graduate Recognition
This program includes the graduate recognition program for summer and fall 2016. Includes photographs, upcoming events, recent publications, and student profiles.
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, Spring 1920 to Spring 2023
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 …
Aircraft Decelerating And Stopping Systems,
2016
Minnesota State University, Mankato
Aircraft Decelerating And Stopping Systems, Nihad E. Daidzic
Aviation Department Publications
FAA Safety Seminar (GL1572070) held at Minnesota State University, Mankato Wiecking Center Auditorium at 18:30 CST on Thursday, November 10, 2016.
Brakes, Thrust Reversers, Beta Props, Spoilers And Life Dumps All Help In Deceleration Of Jets And Turboprops,
2016
Minnesota State University, Mankato
Brakes, Thrust Reversers, Beta Props, Spoilers And Life Dumps All Help In Deceleration Of Jets And Turboprops, Nihad E. Daidzic
Aviation Department Publications
No abstract provided.
Development Of A Thrust Stand For Micro-Electric Propulsion,
2016
University of Alabama in Huntsville
Development Of A Thrust Stand For Micro-Electric Propulsion, Chloe Mcfadden, Kurt Polzin
Von Braun Symposium Student Posters
No abstract provided.
Electromagnetic Forcing As A Damping Method For Combustion Instabilities,
2016
University of Alabama in Huntsville
Electromagnetic Forcing As A Damping Method For Combustion Instabilities, Bradley Henderson, Gabriel Xu
Von Braun Symposium Student Posters
No abstract provided.
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.
Climb Performance Of Business Jets,
2016
Minnesota State University, Mankato
Climb Performance Of Business Jets, Nihad E. Daidzic
Aviation Department Publications
No abstract provided.
Anisoplanatic Electromagnetic Image Propagation Through Narrow Or Extended Phase Turbulence Using Altitude-Dependent Structure Parameter,
2016
University of Dayton
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 …
Design And Experimentation Of A Premixed Rotating Detonation Engine,
2016
Air Force Institute of Technology
Design And Experimentation Of A Premixed Rotating Detonation Engine, Ionio Q. Andrus
Theses and Dissertations
Desire for a more efficient air breathing engine has shifted research attention to the Rotating Detonation Engine (RDE). Detonation is a more efficient combustion process than deflagration and provides a pressure gain. The RDE detonation cycle occurs in a compact volume to produce a high specific impulse engine. Computational fluid dynamic (CFD) models have predicted higher specific impulse and detonation wave speeds than has been seen in experimental RDE. The CFD models frequently assume premixed reactants and ignore inlet geometries to facilitate rapid computation. An experimental premixed RDE was sought to test if the premixed assumption in CFD was the …
Design, Manufacturing, And Testing Of A Small Through-Flow Wave For Use Within The Brayton Cycle,
2016
Air Force Institute of Technology
Design, Manufacturing, And Testing Of A Small Through-Flow Wave For Use Within The Brayton Cycle, Micahel J. Mcclearn
Theses and Dissertations
With the ever growing popularity of drones and other unmanned aerial vehicles for military, commercial, and private usage, there is a desire to improve performance in terms of range, altitude, and flight speed. Current technology uses either electric motors or internal combustion engines: both piston and jet engine types. These sorts of engines undergo significant efficiency degradation as their size decreases. While some efficiency may be recovered via intensive design studies, the cycles are approaching the limit to their operating physics. A possible solution to this is to change the operating physics to something more immune to scaling losses; a …
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 …
Multi-Stage Axial Compressor With Counter-Rotation Using Accessory Drive,
2016
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.
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% of the …
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
Doctoral Dissertations and Master's 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 impingement …
Localized Plasma Measurement During Instability Modes In A Hall Thruster,
2016
Air Force Institute of Technology
Localized Plasma Measurement During Instability Modes In A Hall Thruster, David A. Cunningham
Theses and Dissertations
Hall thrusters are a key technology for current and future unmanned satellites, striking a balance between thrust and fuel economy suitable for many mission profiles of interest. Despite their extensive flight heritage and a large body of research, many phenomena occurring in the plasma discharge of Hall thrusters are not well understood. A combination of intrusive and non-intrusive measurement techniques were used to investigate the properties of the exhaust plume of two Hall thrusters and correlate optical characteristics of oscillating modes with the plasma potential and azimuthal current distribution during those modes. A strong trend was found associating the optical …
Enhanced Flow Migration In Full Annular Ultra Compact Combustor,
2016
Air Force Institute of Technology
Enhanced Flow Migration In Full Annular Ultra Compact Combustor, Nicholas A. Gilbert
Theses and Dissertations
Since combustion efficiency in modern jet engines has stabilized, attention has turned to improving the combustor by improving the thrust-to-weight ratio. The Ultra Compact Combustor (UCC) is a means to reduce the weight of the combustor while ensuring exhaust meets increasingly stringent government emission standards. Combustion occurs within the UCC under a g-load in the circumferential direction, which maintains combustion efficiency while decreasing axial combustor length. Previous analysis optimized the combustion chamber flame characteristics with a common upstream air source. Previously, issues for the UCC were inspired by integration into a traditional axial turbojet. The focus of this investigation was …
