Morehead State University
California Polytechnic State University, San Luis Obispo
University of Massachusetts Amherst
University of Tennessee, Knoxville
Georgia Institute of Technology
University of Akron Main Campus
Arizona Hyperloop: The Fifth Mode Of Transportation,
2020
Embry-Riddle Aeronautical University
Arizona Hyperloop: The Fifth Mode Of Transportation, Eleanor Pahl, Matthieu Rada
Discovery Day - Prescott
Arizona Hyperloop is a coalition between Embry-Riddle Aeronautical University and Arizona State University students competing in Elon Musk’s annual SpaceX Hyperloop Pod Competition. Hyperloop is the proposed “Fifth Mode of Transportation” - coined “a cross between a Concorde, a rail gun, and an air hockey table.” A hyperloop pod levitates and travels at nearly the speed of sound inside a vacuum tube, which eliminates air resistance. Musk hosts the annual competition to university students to encourage the evolution of urban transportation. The goal is to design, build, and race the fastest prototype pod at SpaceX’s mile-long test track in ...
Sae Aero West Heavy Lift Competition Team - Eaglenautics,
2020
Embry-Riddle Aeronautical University
Sae Aero West Heavy Lift Competition Team - Eaglenautics, Anthony Pirone, Evan Stuart, Jessica Millard, Nathaniel Scott
Discovery Day - Prescott
ERAU’s SAE Aero Design West Competition team encourages students of all majors who have an interest in the design of heavy-lift cargo and passenger aircraft to design, build, and fly a large RC aircraft to meet a new set of regulations each competition year. Since the team, Eaglenautics, was founded in 2017 it has successfully been to competition once in April 2019 in California. The team’s aircraft flew 4 out of 5 flight rounds, passed all technical inspections, and is now on display in ERAU’s Aero-Fab in the AXFAB. The 2020 competition requirements are unique in that ...
Developing A Uas-Deployable Methane Sensor Using Low-Cost Modular Open-Source Components,
2020
The University of Akron
Developing A Uas-Deployable Methane Sensor Using Low-Cost Modular Open-Source Components, Gavin Demali
Williams Honors College, Honors Research Projects
This project aimed to develop a methane sensor for deployment on an unmanned aerial system (UAS), or drone, platform. This design is centered around low cost, commercially available modular hardware components and open source software libraries. Once successfully developed, this system was deployed at the Bath Nature Preserve in Bath Township, Summit County Ohio in order to detect any potential on site fugitive methane emissions in the vicinity of the oil and gas infrastructure present. The deliverables of this project (i.e. the data collected at BNP) will be given to the land managers there to better inform future management ...
Atv Dynamics And Pediatric Rider Safety,
2020
University of Kentucky
Atv Dynamics And Pediatric Rider Safety, James T. Auxier Ii
Theses and Dissertations--Biomedical Engineering
It has been observed through numerous academic and governmental agency studies that pediatric all-terrain vehicle ridership carries significant risk of injury and death. While no doubt valuable to safety, the post-hoc approach employed in these studies does little to explain the why and how behind the risk factors. Furthermore, there has been no prolonged, widespread, organized, and concerted effort to reconstruct and catalog the details and causes of the large (20,000+) number of ATV-related injuries that occur each year as has been done for road-based motor vehicle accidents. This dissertation takes the opposite approach from a meta-analysis and instead ...
Design Of Banner Tow Mechanism For Bush Plane,
2020
The University of Akron
Design Of Banner Tow Mechanism For Bush Plane, Kyle Ciarrone, Ivan Martin, Rishabh Gadi, Tyler Brandt
Williams Honors College, Honors Research Projects
The 2019-2020 AIAA DBF objective was to design, build, and test a banner-towing bush plane that carries wooden passengers and luggage. Senior members on the team undertook the creation of the banner tow mechanism subsystem as their senior design project on behalf of the design team due to the challenge of its mechanical design and the aerodynamic considerations regarding its placement and enclosure aboard the aircraft. The competition as well as access to campus resources were canceled due to COVID-19, so full testing and integration of the mechanism was not achieved. However, the engineering design process was experienced from the ...
Performance Enhancement And Characterization Of An Electromagnetic Railgun,
2019
California Polytechnic State University, San Luis Obispo
Performance Enhancement And Characterization Of An Electromagnetic Railgun, Paul M. Gilles
Master's Theses and Project Reports
Collision with orbital debris poses a serious threat to spacecraft and astronauts. Hypervelocity impacts resulting from collisions mean that objects with a mass less than 1g can cause mission-ending damage to spacecraft. A means of shielding spacecraft against collisions is necessary. A means of testing candidate shielding methods for their efficacy in mitigating hypervelocity impacts is therefore also necessary. Cal Poly’s Electromagnetic Railgun was designed with the goal of creating a laboratory system capable of simulating hypervelocity (≥ 3 km/s) impacts. Due to several factors, the system was not previously capable of high-velocity (≥ 1 km/s) tests. A deficient ...
Design Of The 21-Meter Network Monitor And Control System For Deep Space Network Cross Support,
2019
Morehead State University
Design Of The 21-Meter Network Monitor And Control System For Deep Space Network Cross Support, Sarah E. Wilczewski
Morehead State Theses and Dissertations
A thesis presented to the faculty of the College of Science Morehead State University in Partial Fulfillment of the Requirements for the Degree Master of Science by Sarah E. Wilczewski on September 26, 2019.
Cubesat Astronomy Mission Modeling Using The Horizon Simulation Framework,
2019
California Polytechnic State University, San Luis Obispo
Cubesat Astronomy Mission Modeling Using The Horizon Simulation Framework, Alexander W. Johnson
Master's Theses and Project Reports
The CubeSat Astronomy Network is a proposed system of multiple CubeSat spacecraft capable of performing follow-up observations of astronomical targets of interest. The system is intended to serve as a space-borne platform that can complement existing systems utilized for astronomical research by undergraduate and high school students. Much research and development work has been performed to develop model-based system engineering methodologies and products for CubeSat missions, including the Horizon Simulation Framework. The Horizon Simulation Framework enables the development of system models using the Extended Markup Language (XML), and its simulation program can generate system simulations over model-specified timespans. System requirements ...
Satisfiability Checking For Mission-Time Ltl,
2019
Iowa State University
Satisfiability Checking For Mission-Time Ltl, Jianwen Li, Moshe Y. Vardi, Kristin Y. Rozier
Aerospace Engineering Publications
Mission-time LTL (MLTL) is a bounded variant of MTL over naturals designed to generically specify requirements for mission-based system operation common to aircraft, spacecraft, vehicles, and robots. Despite the utility of MLTL as a specification logic, major gaps remain in analyzing MLTL, e.g., for specification debugging or model checking, centering on the absence of any complete MLTL satisfiability checker. We prove that the MLTL satisfiability checking problem is NEXPTIME-complete and that satisfiability checking MLTL0 , the variant of MLTL where all intervals start at 0, is PSPACE-complete. We introduce translations for MLTL-to-LTL, MLTL-to-LTLf , MLTL-to-SMV, and MLTL-to-SMT, creating four ...
A Homegrown Dsmc-Pic Model For Electric Propulsion,
2019
California Polytechnic State University, San Luis Obispo
A Homegrown Dsmc-Pic Model For Electric Propulsion, Dominic Charles Lunde
Master's Theses and Project Reports
Powering spacecraft with electric propulsion is becoming more common, especially in CubeSat-class satellites. On account of the risk of spacecraft interactions, it is important to have robust analysis and modeling tools of electric propulsion engines, particularly of the plasma plume. The Navier-Stokes equations used in classic continuum computational fluid dynamics do not apply to the rarefied plasma, and therefore another method must be used to model the flow. A good solution is to use the DSMC method, which uses a combination of particle modeling and statistical methods for modeling the simulated molecules. A DSMC simulation known as SINATRA has been ...
Innovative Schematic Concept Analysis For A Space Suit Portable Life Support Subsystem,
2019
Texas Engineering Experiment Station
Innovative Schematic Concept Analysis For A Space Suit Portable Life Support Subsystem, M. Schuller, R. Kobrick, T. Lalk, L. Wiseman, F. Little, Et Al.
Ryan L. Kobrick
Conceptual designs for a space suit Personal Life Support Subsystem (PLSS) were developed and assessed to determine if upgrading the system using new, emerging, or projected technologies to fulfill basic functions would result in mass, volume, or performance improvements. Technologies were identified to satisfy each of the functions of the PLSS in three environments (zero-g, Lunar, and Martian) and in three time frames (2006, 2010, and 2020). The viability of candidate technologies was evaluated using evaluation criteria such as safety, technology readiness, and reliability. System concepts (schematics) were developed for combinations of time frame and environment by assigning specific technologies ...
Defining An Abrasion Index For Lunar Surface Systems As A Function Of Dust Interaction Modes And Variable Concentration Zones,
2019
University of Colorado Boulder
Defining An Abrasion Index For Lunar Surface Systems As A Function Of Dust Interaction Modes And Variable Concentration Zones, Ryan L. Kobrick, David M. Klaus, Kenneth W. Street Jr.
Ryan L. Kobrick
Unexpected issues were encountered during the Apollo era of lunar exploration due to detrimental abrasion of materials upon exposure to the fine-grained, irregular shaped dust on the surface of the Moon. For critical design features involving contact with the lunar surface and for astronaut safety concerns, operational concepts and dust tolerance must be considered in the early phases of mission planning. To systematically define material selection criteria, dust interaction can be characterized by two-body or three-body abrasion testing, and sub-categorically by physical interactions of compression, rolling, sliding and bending representing specific applications within the system. Two-body abrasion occurs when a ...
A Technology Survey Of Emergency Recovery And Flight Termination Systems For Uas,
2019
Embry-Riddle Aeronautical University
A Technology Survey Of Emergency Recovery And Flight Termination Systems For Uas, Richard Stansbury, Wesley Tanis, Timothy Wilson
Richard Stansbury
For safe flight in the National Airspace System (NAS), either under the current interim rules or under anticipated longer-term regulatory guidelines facilitating unmanned aircraft system (UAS) access to the NAS, the UAS must incorporate technologies and flight procedures to ensure that neither people nor property in the air, on the ground, or on or in the water are endangered by the failure of an onboard component, by inappropriate unmanned aircraft (UA) response to pilot commands, or by inadvertent entry by the UA into prohibited airspace. The aircraft must be equipped with emergency recovery (ER) procedures and technologies that ensure that ...
System Architecture Design And Development For A Reusable Lunar Lander,
2019
University of Tennessee, Knoxville
System Architecture Design And Development For A Reusable Lunar Lander, Chad Batten, Camille E. Bergin, Aaron Crigger, Darryl Harris, Gillian Suzanne Mcglothin
Chancellor’s Honors Program Projects
No abstract provided.
Comparison Of Induced And Parasitic Drag On Wings With Minimum Induced Drag,
2019
Utah State University
Comparison Of Induced And Parasitic Drag On Wings With Minimum Induced Drag, Sarah A. Abdel-Motaleb
All Graduate Plan B and other Reports
Minimizing the induced drag for steady level flight is a variational problem that requires solving for the optimum lift distribution given a set of design constraints. From lifting-line theory, minimizing the induced drag is, in part, achieved by varying the Fourier coefficients used to describe the section lift. The elliptic lift distribution minimizes the induced drag for a wing with fixed weight and wingspan by setting all but the first coefficient to zero. If wingspan is allowed to vary, a negative third Fourier coefficient is utilized to reach an optimum lift distribution that further reduces the induced drag for stress-limited ...
Extreme Altitude Search And Rescue Helicopter,
2019
Kennesaw State University
Extreme Altitude Search And Rescue Helicopter, Matthew J. De Sieno, Anthony Chavarria, David Stuver, Zach Boss
Senior Design Project For Engineers
The goal of this design was to develop an extreme altitude rescue helicopter capable of retrieving hikers stranded on top of Mount Everest. Using the Eurocopter AS350 as a baseline, a conceptual model was produced that is fully capable of hovering and delivering forward flight at the desired altitude of 8,848 meters. Combined blade element momentum theory, proper airfoil selection, and forward flight calculations were utilized in order to optimize the rotor for the given flight conditions on top of Mount Everest. Conceptual fluid dynamics and CAD modeling aided in the process of visually designing the fuselage and rotor ...
New Design Of An Electronic Power System For The Cosmic X-Ray Background Nanosatellite-3,
2019
Morehead State University
New Design Of An Electronic Power System For The Cosmic X-Ray Background Nanosatellite-3, Christian Joel Ortiz-Huertas
Morehead State Theses and Dissertations
A thesis presented to the faculty of the College of Science Morehead State University in partial fulfillment of the requirements for the Degree of Master of Science by Christian Joel Ortiz Huertas on April 24, 2019.
Incidence Of An Astronaut Not Sealing The Pressure Garment Visor On Reentry,
2019
Portland State University
Incidence Of An Astronaut Not Sealing The Pressure Garment Visor On Reentry, Cameron M. Smith, Trent Tresch
Cameron Smith
Audiovisual records of a Project Mercury pilot’s activities during an orbital flight indicate that his visor was left open during reentry and descent to the sea surface, phases of flight during which cabin pressure loss was to be mitigated by suit pressurization; however, the suit could not have been pressurized with the visor open. Thus, for a presently unknown reason, a critical safety step—sealing the visor and making a pressure suit integrity test before reentry—was overlooked in this flight. Later, Space Shuttle flights were carried out with visors unsealed for much of the launch and landing phases ...
Incidence Of An Astronaut Not Sealing The Pressure Garment Visor On Reentry,
2019
Portland State University
Incidence Of An Astronaut Not Sealing The Pressure Garment Visor On Reentry, Cameron M. Smith, Trent Tresch
Journal of Human Performance in Extreme Environments
Audiovisual records of a Project Mercury pilot’s activities during an orbital flight indicate that his visor was left open during reentry and descent to the sea surface, phases of flight during which cabin pressure loss was to be mitigated by suit pressurization; however, the suit could not have been pressurized with the visor open. Thus, for a presently unknown reason, a critical safety step—sealing the visor and making a pressure suit integrity test before reentry—was overlooked in this flight. Later, Space Shuttle flights were carried out with visors unsealed for much of the launch and landing phases ...
Lasers For Communication And Coordination Control Of Spacecraft Swarms,
2019
University of Arizona
Lasers For Communication And Coordination Control Of Spacecraft Swarms, Himangshu Kalita, Leonard Dean Vance, Vishnu Reddy, Jekan Thanga
Space Traffic Management Conference
Swarms of small spacecraft offer whole new capabilities in Earth observation, global positioning and communications compared to a large monolithic spacecraft. These small spacecraft can provide bigger apertures that increase gain in communication antennas, increase area coverage or effective resolution of distributed cameras and enable persistent observation of ground or space targets. However, there remain important challenges in operating large number of spacecrafts at once. Current methods would require a large number of ground operators monitor and actively control these spacecraft which poses challenges in terms of coordination and control which prevents the technology from scaled up in cost-effective manner ...
