Slipstream Measurements Of Small-Scale Propellers At Low Reynolds Numbers,
2015
Embry-Riddle Aeronautical University
Slipstream Measurements Of Small-Scale Propellers At Low Reynolds Numbers, Robert W. Deters, Gavin K. Ananda, Michael S. Selig
Publications
The continuing growth in the use of small UAVs has required the need to more fully understand the propellers that power them. Part of this understanding is the behavior of the propeller slipstream. Using a 7-hole probe, the slipstreams of several small-scale propellers (diameters of 4.2, 5, and 9 in) were measured in both static (V∞ = 0) and advancing-flow (V∞ > 0) conditions at several locations downstream. For static conditions, as the slipstream expanded downstream, the maximum values of the axial and swirl velocities decreased. The general shape of the static slipstream was also found to be nearly the same …
The “Stratospheric Cricket Keeper” – Developing A Simple“Life-Support” Payload For High-Altitude Balloon Missions,
2015
University of Minnesota - Twin Cities
The “Stratospheric Cricket Keeper” – Developing A Simple“Life-Support” Payload For High-Altitude Balloon Missions, Lucas Kramer, Chad Serba, James Flaten
2017 Academic High Altitude Conference
Exposure to the environmental conditions of “near-space” (AKA the stratosphere) is quickly fatal to nearly all forms of animal life. It is even challenging to build a sealable enclosure that can keep insects (crickets) alive through the dramatic and simultaneous pressure and temperature drops experienced during a high-altitude balloon mission. This poster describes the development of a rugged “cricket keeper” in which we were able to fly crickets to the stratosphere and, quoting the words of JFK, “return (them) safely to the earth!” This “life-support” payload had large windows (for the view!) and included Arduino-logged temperature and pressure sensors, an …
Parafoil Recovery Of A High Altitude Balloon Payload,
2015
Iowa State University
Parafoil Recovery Of A High Altitude Balloon Payload, Chelsea Velasquez, Zachariah Benedict
2017 Academic High Altitude Conference
The Recovery Guidance System is a subproject of Iowa State Universities’ High Altitude Ballooning Experiments in Technology (HABET) group. The system is designed to avoid common hazards during descent including large area objects such as populated areas and roadways, as well as smaller objects such as trees in a field, with an accuracy within tens of meters. RGS provides guidance for the payload using a two servo system aboard the payload in conjunction with GPS and radio communication. Navigation will be handled by a mixture of GPS and video analysis. For guidance, only longitudinal and directional dynamics of the payload-parafoil …
Brief Look At The Environment Of Space,
2015
Morehead State University
Brief Look At The Environment Of Space, Robert J. Twiggs
Robert "Bob" Twiggs STEM Education Collection
A PowerPoint Presentation created by Professor Bob Twiggs titled "Brief Look at the Environment of Space" from June 17, 2015.
Inlet Shape Considerations For Split-Wing Electric Distributed Propulsion,
2015
California Polytechnic State University, San Luis Obispo
Inlet Shape Considerations For Split-Wing Electric Distributed Propulsion, Kurt Vonderhaar Papathakis
Master's Theses
This thesis aims to uncover preliminary design relationships for an inlet of a split-wing electric distributed propulsion regional airliner. Several aspects of the inlet design were investigated, including: the overall thickness of the airfoil section with respect to the chord, inlet throat area, and lip radius. These parameters were investigated using several angles of attack and mass flow rates through the fan. Computational fluid dynamics, with a 2nd Order turbulence model was used and validated against World War II era data from NACA, as those studies were the most pertinent wind tunnel data available. Additionally, other works by Boeing, …
Electric Commuter Multicopter,
2015
California Polytechnic State University, San Luis Obispo
Electric Commuter Multicopter, Marley Hunter Miller, Blake Sperry, Ike Sheppard, Olliver Fredrick Kunz, Sam Juday, Alex O'Hearn, Kyle Seth Kruse, Arthur Norwood, Jarrell Washington
Mechanical Engineering
This document describes the design, analysis, and overall goals of the Electric Commuter Multicopter (ECM) Senior Project. It was presented by Bob Addis and Bill Burner to the senior mechanical engineering class of 2015 at Cal Poly, San Luis Obispo. The progress and development of the project are described in detail and to an extent that an individual or group with similar aspirations can construct their own multicopter or expand upon this one. The goal of this project is to create an Ultralight, as defined by FAA Part 103, commuter multicopter vehicle capable of transporting an individual to and from …
Aerodynamic And Structural Design Of A Winglet For Enhanced Performance Of A Business Jet,
2015
Embry-Riddle Aeronautical University
Aerodynamic And Structural Design Of A Winglet For Enhanced Performance Of A Business Jet, Nicolas El Haddad
Doctoral Dissertations and Master's Theses
The preliminary design of a winglet to improve the range and fuel burn of the Falcon 10 business jet is presented. Twelve candidate geometries were studied varying the cant angle and the span. The configuration offering the best compromise between induced drag reduction, profile drag increase and weight increase due to the winglet structure and necessary wing structural reinforcement was selected. More refined analysis was performed for that winglet with Reynolds averaged Navier-Stokes computational fluid dynamics and finite element analysis. Range and fuel burn were finally calculated for a typical mission using these refined results. The selected winglet, with a …
Unstandard Cubesat/Pocketqube/Tubesat Deployers,
2015
Morehead State University
Unstandard Cubesat/Pocketqube/Tubesat Deployers, Robert J. Twiggs
Robert "Bob" Twiggs STEM Education Collection
A PowerPoint presentation created by Professor Bob Twiggs titled "Unstandard CubeSat/PocketQube/TubeSat Deployers" from April 23, 2015.
Cdtx: Cool Drop Test Experiment,
2015
Morehead State University
Cdtx: Cool Drop Test Experiment, Robert J. Twiggs
Robert "Bob" Twiggs STEM Education Collection
A PowerPoint presentation created by Professor Bob Twiggs titled "CDTX: Cool Drop Test Experiment" from April 7, 2015.
Performance Characteristics Of Fluidic-Based Thrust Augmentation Using A Slot Jet For Unmanned Aerial Vehicle Propulsion,
2015
Old Dominion University
Performance Characteristics Of Fluidic-Based Thrust Augmentation Using A Slot Jet For Unmanned Aerial Vehicle Propulsion, Brendan A. Wiedow
Mechanical & Aerospace Engineering Theses & Dissertations
Currently most small vertical takeoff and landing Unmanned Aerial Vehicles (UA V's) use a quadcopter design by utilizing four exposed blades rotating at high RPMs around a central array of components. The research performed in this thesis is focused on understanding the underlying fluid dynamics of a slot jet through the use of flow entrainment for thrust augmentation with the application to be integrated into a novel UAV system with no external moving parts. Current publicly available quadcopter rotor design type aircraft were used as a basis for the design target weight and power to estimate the amount of thrust …
The Panther: 2015 Aiaa Design Build Fly,
2015
Embry-Riddle Aeronautical University
The Panther: 2015 Aiaa Design Build Fly, Bryce Milnes, Chris Crawford
Publications
The ERAU Prescott chapter of AIAA participated in the 2015 AIAA Design Build Fly competition at Raytheon Missile Systems in Tucson from April 10-12. A remote controlled aircraft meeting and exceeding all competition performance requirements was designed and fabricated by the 30+ students of the team. Additionally, a 60 page report was submitted detailing the project starting from initial considerations and advancing through flight test verification of aircraft capabilities. The success of this project was enabled by the E-Prize and SGA funding received to support our efforts throughout the year. The lessons learned regarding management and planning, engineering design approaches, …
Unmanned Aerial Vehicle (Uav) Propulsion Research: Conceptual Studies Of “Ultra-Compact Shaft-Less Jet Engines” For Next Generation Uavs,
2015
Embry-Riddle Aeronautical University
Unmanned Aerial Vehicle (Uav) Propulsion Research: Conceptual Studies Of “Ultra-Compact Shaft-Less Jet Engines” For Next Generation Uavs, Tyler Eiguren, Trevor Douglas, Tre Buchanan
Publications
Unmanned Aerial Vehicles are becoming more commonly used in today’s society, ranging anywhere from military applications to entertainment for enthusiasts and hobbyists. The complexity of current generation UAV’s propulsive devices, based upon a scaled turbine engine and separate gas & electrically powered rotating fan blades, require regular maintenance for every 24 hours of flight. This added cost coupled with necessary intricate machinery deters UAV designers from such engines, leaving a void in current production. Our research team believes that by combining a simplified alternative compression & combustion process with an electrically driven fan, we can develop an energy efficient, reliable, …
Into Space @ Morehead,
2015
Morehead State University
Into Space @ Morehead, Robert J. Twiggs
Robert "Bob" Twiggs STEM Education Collection
A PowerPoint presentation created by Professor Bob Twiggs titled "Into Space @ Morehead" from March 26, 2015.
Dynamic Response Analysis Of An Icosahedron Shaped Lighter Than Air Vehicle,
2015
Air Force Institute of Technology
Dynamic Response Analysis Of An Icosahedron Shaped Lighter Than Air Vehicle, Lucas W. Just
Theses and Dissertations
The creation of a lighter than air vehicle using an inner vacuum instead of a lifting gas is considered. Specifically, the icosahedron shape is investigated as a design that will enable the structure to achieve positive buoyancy while resisting collapse from the atmospheric pressure applied. This research analyzes the dynamic response characteristics of the design, and examines the accuracy of the finite element model used in previous research by conducting experimental testing. The techniques incorporated in the finite element model are confirmed based on the experimental results using a modal analysis. The experimental setup designed will allow future research on …
Eps & Batteries,
2015
Morehead State University
Eps & Batteries, Jeff Kruth
Robert "Bob" Twiggs STEM Education Collection
Notes written by Jeff Kruth on "EPS & Batteries" from March 12, 2015.
Comparison Of Aircraft Tire Wear With Initial Wheel Rotational Speed,
2015
University of Sussex
Comparison Of Aircraft Tire Wear With Initial Wheel Rotational Speed, Abdurrhman A. Alroqi, Weiji Wang
International Journal of Aviation, Aeronautics, and Aerospace
The impact an aircraft has on its tires when it lands has been problematic practically since the invention of the airplane. Upon touchdown, the tires frequently smoke as rubber burns off and tire material is worn away while the tires slip up to a steady rolling speed. To minimise tire slip, torque or spin mechanisms could be added to each tire assembly to accelerate the tire to match the landing speed. Patents have been registered since the 1940s to improve tire safety and performance, decrease the substantial wear that results from every landing, and save airline companies the cost of …
Experimental Investigation Of Stochastic Parafoil Guidance Using A Graphics Processing Unit,
2015
George Fox University
Experimental Investigation Of Stochastic Parafoil Guidance Using A Graphics Processing Unit, Nathan Slegers, Andrew Brown, Jonathan Rogers
Faculty Publications - Biomedical, Mechanical, and Civil Engineering
Control of autonomous systems subject to stochastic uncertainty is a challenging task. In guided airdrop applications, random wind disturbances play a crucial role in determining landing accuracy and terrain avoidance. This paper describes a stochastic parafoil guidance system which couples uncertainty propagation with optimal control to protect against wind and parameter uncertainty in the presence of impact area obstacles. The algorithm uses real-time Monte Carlo simulation performed on a graphics processing unit (GPU) to evaluate robustness of candidate trajectories in terms of delivery accuracy, obstacle avoidance, and other considerations. Building upon prior theoretical developments, this paper explores performance of the …
Aircraft De-Icing System Using Thermal Conductive Fibers,
2015
Embry-Riddle Aeronautical University
Aircraft De-Icing System Using Thermal Conductive Fibers, Min Soon Park
Doctoral Dissertations and Master's Theses
The accumulation of ice on the leading edges of aircraft wing poses complications for flight control as drag is increased with a tendency for higher relative turbulence over the wing. Pre-emptive and reactive ice removal techniques have been employed in the past by electromechanical, thermal, chemical and pneumatic methods. In this thesis, a carbon fiber fabric is utilized as a heating de-icer for composites aircraft wing surface structures. Two prototypes are constructed, tested to generate temperature profiles, and an appropriate heating voltage is selected for effective de-icing via distinct avenues of heating system configurations. The heat transfer efficiency of the …
Design Methods For Remotely Powered Unmanned Aerial Vehicles,
2015
California Polytechnic State University, San Luis Obispo
Design Methods For Remotely Powered Unmanned Aerial Vehicles, William Beaman Howe
Master's Theses
A method for sizing remotely powered unmanned aerial vehicles is presented to augment the conventional design process. This method allows for unconventionally powered aircraft to become options in trade studies during the initial design phase. A design matrix is created that shows where, and if, a remotely powered vehicle fits within the design space. For given range and power requirements, the design matrix uses historical data to determine whether an internal combustion or electrical system would be most appropriate. Trends in the historical data show that the break in the design space between the two systems is around 30 miles …
A Contribution Toward Better Understanding Of Overbanking Tendency In Fixed-Wing Aircraft,
2015
AAR Aerospace Consulting, LLC
A Contribution Toward Better Understanding Of Overbanking Tendency In Fixed-Wing Aircraft, Nihad E. Daidzic
Journal of Aviation Technology and Engineering
The phenomenon of overbanking tendency for a rigid-body, fixed-wing aircraft is investigated. Overbanking tendency is defined as a spontaneous, unbalanced rolling moment that keeps increasing an airplane’s bank angle in steep turns and must be arrested by opposite aileron action. As stated by the Federal Aviation Administration, the overbanking tendency may lead to a loss of control, especially in instrument meteorological conditions. It was found in this study that the speed differential over wing halves in horizontal turns indeed creates a rolling moment that achieves maximum values for bank angles between 45 and 55 degrees. However, this induced rolling moment …
