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Comparison Of Aircraft Tire Wear With Initial Wheel Rotational Speed, Abdurrhman A. Alroqi, Weiji Wang 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 ...


A Contribution Toward Better Understanding Of Overbanking Tendency In Fixed-Wing Aircraft, Nihad E. Daidzic 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 ...


Structure And A Detailed Analysis Of Various Simulation Results Of Cntfet: A Review, Innovative Research Publications IRP India, Himanshu Gautam, Prateek Bindra 2015 Innovative Research Publications

Structure And A Detailed Analysis Of Various Simulation Results Of Cntfet: A Review, Innovative Research Publications Irp India, Himanshu Gautam, Prateek Bindra

Innovative Research Publications IRP India

A detailed review on the Carbon Nanotube Filed Effect Transistors (CNTFETs) has been given. A little description about what are carbon nanotubes is also been covered. Various simulation results have also been included in this paper in order to provide better understanding about the carbon nanotubes field effect transistors.Characteristic Graphs of a C-CNTFET with n=10. m=11 (diameter=1.4246 nm) have been studied. Threshold voltage of CNTFETs vs n (for m=0) is also simulated. Equivalent high-frequency small-signal circuit model for a Nanotube transistor has also been analyzed. Also current voltage relationship of the CNTFET with respect ...


In Search Of Standards For The Operation Of Small Satellites, Jeremy Straub 2015 SelectedWorks

In Search Of Standards For The Operation Of Small Satellites, Jeremy Straub

Jeremy Straub

This paper considers the need for standards for the operations of small spacecraft. First, it considers a definition for what a small spacecraft is and discusses the elusiveness of this definition. Then, the paper turns to the ‘large space’ community and it examines their fears about small spacecraft as well as the operating paradigms that they are used to and how these drive their expectations for the operations of small spacecraft. Next, a prospective composition for a preliminary set of operating standards is discussed. Finally, a discussion of the benefits of standardization and what the different communities could expect to ...


Openorbiter Mechanical Design: A New Approach To The Design Of A 1-U Cubesat, Benjamin Kading, Jeremy Straub, Ronald Marsh 2015 SelectedWorks

Openorbiter Mechanical Design: A New Approach To The Design Of A 1-U Cubesat, Benjamin Kading, Jeremy Straub, Ronald Marsh

Jeremy Straub

The OpenOrbiter Small Spacecraft Development Initiative is working to create a set of designs and implementation instructions for a 1-U CubeSat, called the Open Prototype for Educational NanoSats. These designs target a total parts cost of below USD $5,000. This design will be made publically available to facilitate its use by others, with or without modification. A ‘side slotted’ CubeSat design (where main circuit boards are placed in slots between the rails on the outside) has been developed for OpenOrbiter. This paper discusses the design choices that were made during the mechanical structure development of the OpenOrbiter CubeSat design ...


Intelligent Water Drops Algorithm For Coordinating Between Cluster Spacecraft In A Communications-Denied Environment, Jeremy Straub 2015 SelectedWorks

Intelligent Water Drops Algorithm For Coordinating Between Cluster Spacecraft In A Communications-Denied Environment, Jeremy Straub

Jeremy Straub

This paper presents a modification of Shah-Hosseini’s Intelligent Water Drops (IWD) technique that can be utilized for collaborative control of multiple spacecraft in environments where communications are limited, intermittent or denied. It presents Shah- Hosseini’s base IWD algorithm as well as refinements thereof, which simplify it, making it more suitable for more computationally constrained environments (such as small spacecraft and UAVs). A framework for testing the proposed approach as well as several implementation impediments are discussed.


Characterization Of Fillite As A Planetary Soil Simulant In Support Of Rover Mobility Assessment In High-Sinkage/High-Slip Environments, Michael Edwards 2015 University of Vermont

Characterization Of Fillite As A Planetary Soil Simulant In Support Of Rover Mobility Assessment In High-Sinkage/High-Slip Environments, Michael Edwards

Graduate College Dissertations and Theses

This thesis presents the results of a research program characterizing a soil simulant called Fillite, which is composed of alumino-silicate hollow microspheres harvested from the pulverized fuel ash of coal-fired power plants. Fillite is available in large quantities at a reasonable cost and it is chemically inert. Fillite has been selected by the National Aeronautics and Space Administration (NASA) Glenn Research Center to simulate high-sinkage/high-slip environment in a large test bed such as the ones encountered by the Spirit rover on Mars in 2009 when it became entrapped in a pocket of soft, loose regolith on Mars. The terms ...


Numerical Investigation On Charring Ablator Geometric Effects: Study Of Stardust Sample Return Capsule Heat Shield, Haoyue Weng, Alexandre Martin 2015 University of Kentucky

Numerical Investigation On Charring Ablator Geometric Effects: Study Of Stardust Sample Return Capsule Heat Shield, Haoyue Weng, Alexandre Martin

Mechanical Engineering Faculty Publications

Sample geometry is very influential in small charring ablative articles where 1D assumption might not be accurate. In heat shield design, 1D is often assumed since the nose radius is much larger than the thickness of charring. Whether the 1D assumption is valid for the heat shield is unknown. Therefore, the geometric effects of Stardust sample return capsule heat shield are numerically studied using a material response program. The developed computer program models material charring, conductive heat transfer, surface energy balance, pyrolysis gas transport and orthotropic material properties in 3D Cartesian coordinates. Simulation results show that the centerline temperatures predicted ...


Wind And Thermal Effects On Ground Mounted Photovoltaic (Pv) Panels, Chowdhury Mohammad Jubayer 2014 The University of Western Ontario

Wind And Thermal Effects On Ground Mounted Photovoltaic (Pv) Panels, Chowdhury Mohammad Jubayer

University of Western Ontario - Electronic Thesis and Dissertation Repository

A combination of Computational Fluid Dynamics (CFD) simulations and wind tunnel experiments are carried out to investigate the effects of wind on the aerodynamic loading and heat transfer of a ground mounted stand-alone photovoltaic (PV) panel with tilt angle of 25o in open country atmospheric boundary layer. Several azimuthal wind directions are considered: Southern 0o, Southwest 45o, Northwest 135o and Northern 180o. Three dimensional Reynolds-Averaged Navier-Stokes (RANS) approaches with an unsteady solver using Shear Stress Transport (SST) k-ω turbulence closure are employed for the CFD simulations, whereas Particle Image Velocimetry (PIV) and Hot Wire Anemometry ...


Heat Transfer Enhancement And Applications Of Femtosecond Laser Processed Metallic Surfaces, Corey M. Kruse 2014 University of Nebraska-Lincoln

Heat Transfer Enhancement And Applications Of Femtosecond Laser Processed Metallic Surfaces, Corey M. Kruse

Mechanical (and Materials) Engineering -- Dissertations, Theses, and Student Research

In the present work, functionalized 304 stainless steel metallic surfaces were created with the use of a Femtosecond Laser Surface Processing (FLSP) technique. The laser processing technique produces self-organized micro/nanostructures on the surface. The heat transfer performance of various FLSP functionalized surfaces were characterized through pool boiling and Leidenfrost experiments. Enhancement in both the nucleate and film boiling heat transfer were observed through an increase of the critical heat flux and heat transfer coefficient as well as shifts in the Leidenfrost temperature respectively. For both experiments, a polished reference sample was used as a baseline line to compare against ...


Helical Models Of The Bidirectional Vortex In A Conical Geometry, Timothy Andrew Barber 2014 University of Tennessee - Knoxville

Helical Models Of The Bidirectional Vortex In A Conical Geometry, Timothy Andrew Barber

Doctoral Dissertations

This dissertation represents the descriptive and analytical breakdown of two new fluid dynamics solutions for vortex motion. Both solutions model the bidirectional vortex within a conical geometry. The first explored solution satisfies a simple Beltramian characteristic, where the Lamb vector is identically zero. The second solution is of the generalized Beltramian type, which fulfills the condition that the curl of the Lamb vector is equal to zero. The two Beltramian solutions describe the axisymmetric, double helical motion often found in industrial cyclone separators. Other applications include cone-shaped, vortex-driven combustion chambers and the swirling flow through conical devices. Both solutions are ...


Experiment And Simulation Of The Acoustic Signature Of Fatigued-Cracked Gears In A Two-Stage Gearbox, Matthew James Ostiguy 2014 California Polytechnic State University - San Luis Obispo

Experiment And Simulation Of The Acoustic Signature Of Fatigued-Cracked Gears In A Two-Stage Gearbox, Matthew James Ostiguy

Master's Theses and Project Reports

This thesis focuses on the development of a health monitoring system for gearbox transmissions. This was accomplished by developing and understanding a two-stage gearbox computer model that emulates an actual gearbox test rig. The computer model contains actual gearbox geometry, flexible shafts, bearings, gear contact forces, input motor torque, output brake torque, and realistic gearbox imbalance. The gear contact force of each gear stage and the input bearing translational acceleration were the main outputs compared between a healthy gearbox and damaged gearbox computer model. The damage of focus was a fatigue crack on the input pinion gear. A sideband energy ...


The Critical Role Of Cubesat Spacecraft In A Multi-Tier Mission For Mars Exploration, Jeremy Straub 2014 SelectedWorks

The Critical Role Of Cubesat Spacecraft In A Multi-Tier Mission For Mars Exploration, Jeremy Straub

Jeremy Straub

A multi-tier architecture is under development (with similar craft heterogeneity to Fink's work on ‘tier scalable’ missions) which will facilitate autonomous local control of multiple heterogeneous craft. This mission architecture has been developed with a Mars mission in mind and has included CubeSats in a variety of critical mission roles.

Two concepts will be presented: the addition of CubeSats to a larger-scale multi-tier mission, where the CubeSats serve a supporting role and a mission driven by CubeSat orbital capabilities. In the first, CubeSats are utilized to augment the area of spatial coverage that can be obtained and the temporal ...


Achieving Global Range In Future Subsonic And Supersonic Airplanes, Nihad E. Daidzic Ph.D., Sc.D. 2014 AAR Aerospace Consulting, LLC

Achieving Global Range In Future Subsonic And Supersonic Airplanes, Nihad E. Daidzic Ph.D., Sc.D.

International Journal of Aviation, Aeronautics, and Aerospace

No commercial airplane in service today is able to fly half great-circle distances over the globe and achieve the non-stop or the global range to any antipodal location on Earth. A subsonic jetliner has the optimum cruising speed at Mach numbers approaching the drag divergence Mach number while still preserving relatively high aerodynamic efficiency. Various fuel-flow laws were used to investigate the cruise performance of subsonic and supersonic aircraft. The effect of wind and aircraft weight and how it affects the optimal cruising airspeed was investigated. Of all different operational cruising techniques, the cruise-climb at high Mach numbers is the ...


The History Of Space Debris, Loretta Hall 2014 Author

The History Of Space Debris, Loretta Hall

Space Traffic Management Conference

This paper examines what space debris consists of and where it came from. In 1958, astronomer Clyde Tombaugh published the results of his research into the existence of natural debris near the Earth, concluding that no such debris existed. During the ensuing fifty-five years, man-made debris has been accumulating to the point that it threatens launches, active satellites, and the International Space Station. NASA reported that as of 2013, more than 21,000 pieces the size of a softball or larger were being tracked, as were about 500,000 pieces at least the size of a marble and “many millions ...


An Integrated Approach To Orbital Debris Research And Management, Marshall H. Kaplan 2014 Center for Orbital Debris Education and Research (CODER)

An Integrated Approach To Orbital Debris Research And Management, Marshall H. Kaplan

Space Traffic Management Conference

A viable space traffic management program faces a great barrier caused by the ever-increasing number and variety of orbiting objects ranging in size from a few microns to several meters. Although several international agreements to limit the growth rate of orbital debris are in place, the risk of damage and destruction to active satellites is continually rising. The urgency of this situation was highlighted by the 2007 Chinese ASAT test and the collision of Iridium and Cosmos satellites in 2009. Although many debris removal techniques have been posited none have been implemented. Unless a space debris reduction program is undertaken ...


Where Is Space? And Why Does That Matter?, Bhavya Lal, Emily Nightingale 2014 Science and Technology Policy Institute

Where Is Space? And Why Does That Matter?, Bhavya Lal, Emily Nightingale

Space Traffic Management Conference

Despite decades of debate on the topic, there is no consensus on what, precisely, constitutes the boundary between airspace and outer space. The topic is mired in legal and political conundrums, and the easy solution to-date has been to not agree on a definition of space. Lack of a definition, some experts claim, has not limited space-based activities, and therefore is not a hurdle that must be overcome. There are increasing calls however in light of increasing (and expectations of increasing) space traffic, both orbital and sub-orbital. This paper summarizes the proposed delimitation of space, the current debate on whether ...


Aerodynamic Optimization Of Box Wing – A Case Study, Adeel Khalid, Parth Kumar 2014 Embry-Riddle Aeronautical University - Worldwide

Aerodynamic Optimization Of Box Wing – A Case Study, Adeel Khalid, Parth Kumar

International Journal of Aviation, Aeronautics, and Aerospace

The optimization of a possible medium range box wing commercial airliner is presented in three stages. Preliminary research is used to determine various parameters for a potential box wing model, and a baseline model is designed in Autodesk Inventor, based upon the cantilever Airbus A330-200, an aircraft of a similar role. The Computational Fluid Dynamics (CFD) software used in this project is Dassault Systèmes SolidWorks, which is validated through comparing the NACA 0009 airfoil lift and drag polars with published results. The first stage of optimization is performed on the airfoil shape, with 8 different designs being tested against the ...


Improving Airplane Touchdown Control By Utilizing The Adverse Elevator Effect, Nihad E. Daidzic Ph.D., Sc.D. 2014 AAR Aerospace Consulting, LLC

Improving Airplane Touchdown Control By Utilizing The Adverse Elevator Effect, Nihad E. Daidzic Ph.D., Sc.D.

International Journal of Aviation, Aeronautics, and Aerospace

The main objective of this original research article is to understand the short-term dynamic behavior of the transport-category airplane during landing flare elevator control application. Increasing the pitch angle to arrest the sink rate, the elevator will have to produce negative lift to rotate the airplane’s nose upward. This has an immediate adverse effect of initially accelerating airplane downward. A mathematical model of landing flare based on the flat-Earth longitudinal dynamics of rigid airplane was developed which is realistic only on very short time-scales as pitch stiffness and damping were neglected. Pilot control scenarios using impulse and step elevator ...


Rocket Flight Path, Jamie L. Waters 2014 University of South Florida

Rocket Flight Path, Jamie L. Waters

Jamie L Waters

This project uses Newton’s Second Law of Motion, Euler’s method, basic physics, and basic calculus to model the flight path of a rocket. From this project, one can find the height and velocity at any point from launch to the maximum altitude, apogee. Once complete this can be compared to what the actual values were to see if the method is a plausible way of estimation. The rocket used in this project is modeled after Bullistic-1 which was launched by the Society of Aeronautics and Rocketry at the University of South Florida.


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