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Open Where You Are Webinar
No full textOpen Where You Are: Ideas to Engage with Open Education at Every Level
Join Cassandra Konz, Heather Crane, and Eleni Rammos to learn about open education and how faculty can incorporate it into their teaching, no matter how much time or experience they have with open!
This webinar will go over the basic ideas behind open education, how it can support your work as faculty, and many different ways to engage with open, from basic to advanced. This webinar will feature ideas that you can incorporate at any time, and real-world examples from your fellow ERAU faculty.
This webinar is part of Open Education Week 2025. Explore more from the event at https://commons.erau.edu/oe-week/2025/
ERAU Eaglenautics - SAE AeroDesign Team LLAMAS (Large Lifting Aerodynamic Modular Aircraft Systems)
No full textTeam LLAMAS has designed and manufactured an aircraft for the SAE Aero Design West competition held in April 2025 in Van Nuys, California. The competition mission called for building an aircraft that maximized payload capacity while adhering to several mission and design requirements. Among these requirements was the ability to take off within 100 ft and land within 400 ft. No specific flight path was specified by the competition, but the aircraft had to make at least one 360-degree lap prior to landing for its flight to be scored. The aircraft wingspan had to be between 10 and 15 ft and be able to disassemble into 4 ft by 4 ft by 4 ft sections. The propulsion system was limited to 750 W, and fiber-reinforced plastics were not allowed by the competition. The aircraft Team LLAMAS designed had a maximum takeoff weight of 55 lb with a payload weight of 23 lb.It was primarily constructed from balsa wood with an aluminum wing spar and tail boom. The exterior of the aircraft was covered with Monokote film. The wingspan of the aircraft was 15 ft to maximize on bonus points, and disassembled into 10 different subsections. The aircraft could take off in 85 ft, land in 150 ft, and met all the competition requirements
Development of Kerosene and Liquid Oxygen Gas Generator
No full textGas Generator are a subcomponent of turbopumps, which are needed to power large rocket engines. Low thrust (under 5,000 lbf) rocket engines typically use what is known as a blowdown type feed system to pressurize propellants and inject them into the chamber. A blowdown system uses high pressure gases like nitrogen or helium to pressurize the entire propellant tank. This simple approach is great for low thrust engines and small tank sizes. As engine thrust, and tank sizes grow, the system becomes heavier and begins to encounter multiple technical issues. For larger engines, turbopumps offer significant mass savings, at the expense of drastically increased complexity. Turbopumps are use pumps, driven by a turbine, to pressurize the propellants used in engines. Gas Generators generate a high energy flow of gas to power the turbine, usually by combusting the same propellants as the rocket engine they power. Rocket engines and gas generators have many similarities; however, gas generators have their own set of unique technical problems, on top of the typical problems contributed to rocket engines. The position of the gas generator upstream of a turbine, necessitates better mixing of propellants and the combustion products used than in a rocket engines chamber. Additionally, the temperature of the gases must be much lower than that of a typical engine, leading to extreme oxidizer / fuel ratios. Janus R, a 3,000lbf kerosene and liquid oxygen rocket engine designed by ERAU students was used to set requirements for the preliminary design of a small turbopump, from which the requirements for the design of a kerosene and liquid oxygen gas generator were derived. The preliminary and critical design of the gas generator are taking place this spring, followed by manufacturing, in preparation for a test campaign in the fall semester
Statistical Analysis of Air Traffic Density and Runway Incursions
Get PDFRecently, aircraft accidents and runway incursions have surged due to multiple contributing factors, including increased air traffic density, human error, and operational complexities at major airports. The growing number of near-miss incidents and incursions underscores the urgent need for data-driven analysis to mitigate aviation risks. This study investigates the relationship between air traffic density and the frequency of runway incursions in Class B airspace, utilizing real-world data collected over the past year. The research specifically examines the role of human factors, such as fatigue-related incidents and miscommunication, and the impact of technological advancements, including ASDE-X and Runway Status Lights (RWSL), in mitigating risks. A one-way ANOVA test was conducted using StatCrunch to determine whether variations in air traffic density significantly affect runway incursions. The findings provide valuable insights into aviation safety and offer recommendations for improving airport operations, traffic control procedures, and technological interventions to reduce runway incursions
Lockheed Martin Ethics in Engineering Competition
No full textThe Lockheed Martin Ethics in Engineering Competition held in Bethesda, Maryland connects engineering students nationwide to develop professional communication skills and foster discussion of ethical values. By working together to solve technical and ethical challenges, future engineers develop important skills for the workplace that supplement their university education.
The 2025 Ethics in Engineering Competition led competitors to research AI decision making processes in wildland fire management, and the Implications of leaving decisions involving human lives to AI. Teams were required to present a solution that Integrated AI responsibly into fire management, while navigating workplace challenges. ERAU – Prescott students networked with Lockheed Martin mentors and other students nationwide while developing valuable workplace skills: Navigating conflict, voicing ethical values, and communicating technically and professionally
Colliding Winds and Dust Shells: Resolving Wolf-Rayet Binary Stars
No full textWolf-Rayet (WR) stars are massive stars that have lost their outer hydrogen layers and often are rich in carbon. When in systems with multiple high massloss rate stars, such as O stars, the colliding winds between the stars can be linked to dust formation. One of the WRs of particular interest is CV Serpentis, which is a binary star system consisting of a WR and an O star. The stars eclipse and orbit each other in a circular path, but a deeper analysis shows that only some of the wavelengths of light decrease in intensity during eclipses and that the dust formed by the stars clump unpredictably instead being distributed in a spiral. To explain those strange behaviors, we are analyzing the spectra in hopes of finding that the velocities of the stars orbiting each other has changed over time. That discovery would indicate that there is a third, previously unknown star in the system. Other stars we research are WR112, WR48a, WR125, and WR137. Each of those star systems have O star partners, and interactions between the O star and the WR star via shock waves creates shells of dust. Out of these four, only one of them has had an in-depth modelling of its dust\u27s positions and densities. Simulating the dust\u27s behavior can give information about the temperature of the WR star, the velocity of the stellar wind, and the mass of the dust. These attributes link back to being able to discover the origins of the dust, including how exactly and where it gets formed, which is a massive unknown amongst many WR stars