A Photogrammetry-Based Hybrid System For Dynamic Tracking And Measurement, 2010 Air Force Institute of Technology
A Photogrammetry-Based Hybrid System For Dynamic Tracking And Measurement, Daniel P. Magree
Theses and Dissertations
Noncontact measurements of lightweight flexible aerospace structures present several challenges. Objects are usually mounted on a test stand because current noncontact measurement techniques require that the net motion of the object be zero. However, it is often desirable to take measurements of the object under operational conditions, and in the case of miniature aerial vehicles (MAVs) and deploying space structures, the test article will undergo significant translational motion. This thesis describes a hybrid noncontact measurement system which will enable measurement of structural kinematics of an object freely moving about a volume. By using a real-time videogrammetry system, a set of ...
An Integrity Framework For Image-Based Navigation Systems, 2010 Air Force Institute of Technology
An Integrity Framework For Image-Based Navigation Systems, Craig D. Larson
Theses and Dissertations
This work first examines fundamental differences between measurement models established for GPS and those of proposed image-based navigation systems. In contrast to single value per satellite GPS pseudorange measurements, image measurements are inherently angle-based and represent pixel coordinate pairs for each mapped target. Thus, in the image-based case, special consideration must be given to the units of the transformations between the states and measurements, and also to the fact that multiple rows of the observation matrix relate to particular error states. An algorithm is developed to instantiate a framework for image-based integrity analogous to that of GPS RAIM. The algorithm ...
Velocity Plume Profiles For Hall Thrusters Using Laser Diagnostic, 2010 Air Force Institute of Technology
Velocity Plume Profiles For Hall Thrusters Using Laser Diagnostic, Daniel B. Lee
Theses and Dissertations
This research built a non-intrusive laser diagnostic tool using Laser Induced Fluorescence (LIF) and absorption techniques to measure the velocity and density plume profiles of low powered Hall thrusters. This tool was then applied to a Busek 200W Hall thruster to validate the performance against previous research on the same thruster. A laser frequency sweep through 834.72 nm produced LIF signals for ionized xenon –collected at 541.9 nm – in the thruster plume and absorption data outside the plume at a neutral transition at 834.68 nm. The absorption data provided a baseline reference to calculate the axial and ...
Matlab Structural Analysis Code For String Wing Box Structure, 2010 California Polytechnic State University - San Luis Obispo
Matlab Structural Analysis Code For String Wing Box Structure, Sean Brown
This report outlines the method used for analysis of a wing box structure for the experimental “stringy” wing structure often used in light RC aircraft. This code is able to find the displacement of each joint, and the stress and forces in each member of the truss structure. It also has the features of load and structure visualization, Kevlar string removal, user-defined point and distributed loading functions, and user-defined failure criteria function. This method and resulting code is meant for use in the support of the Human Powered Helicopter project being undertaken by the Aerospace and Mechanical Engineering Department at ...
Analysis Of A Passive Flow Control Device Via Flow Visualization Techniques, 2010 California Polytechnic State University - San Luis Obispo
Analysis Of A Passive Flow Control Device Via Flow Visualization Techniques, Cheryl R. Graham, Shi (Peter) Huang
This report details an experiment done to verify the effectiveness of a passive flow control system on a two-dimensional bluff body, blunt trailing edge model in controlling wake dimension and Karman vortex sheds. An earlier experiment by Park, et.al. performed analysis via wind tunnel pressure testing and computerized model to determine the ideal proportions of such a tab design and identify the flow properties responsible for the potential drag reduction. To obtain visual verification of the existence of these concepts, a bluff body model proportionally identical to the one used by Park, et.al., was designed and tested ...
Some Systemic Issues In The Development Of The Aerospace Industry Technical Workforce Of The Future, 2010 The Boeing Company
Some Systemic Issues In The Development Of The Aerospace Industry Technical Workforce Of The Future, John H. Mcmasters, Russell M. Cummings
Russell M. Cummings
This paper is a continuation of the authors’ previous examinations of a suite of issues surrounding the putative decline in aeronautics in this country. The purpose of this paper is to discuss three specific issues believed to be of particular importance to the future of our industry. The first is the question of how many engineers we may need in our future as we confront the problem of an aging workforce and the globalization of our industry. The second is the question of what skills and abilities these engineers will need to possess as the overall industry continues to evolve ...
Comparisons Of Computational Fluid Dynamics Solutions Of Static And Manoeuvering Fighter Aircraft With Flight Test Data, 2010 United States Air Force Academy
Comparisons Of Computational Fluid Dynamics Solutions Of Static And Manoeuvering Fighter Aircraft With Flight Test Data, David R. Mcdaniel, Russell M. Cummings, K. Bergeron, Scott A. Morton, J. P. Dean
Russell M. Cummings
As the capabilities of computational fluid dynamics (CFD) to model full aircraft configurations improve, and the speeds of massively parallel machines increase, it is expected that CFD simulations will be used more and more to steer or in some cases even replace traditional flight test analyses. The mission of the US Air Force SEEK EAGLE office is to clear any new weapon configurations and loadings for operational use. As more complex weapons are developed and highly asymmetric loadings are requested, the SEEK EAGLE office is tasked with providing operational clearances for literally thousands of different flight configurations. High-fidelity CFD simulations ...
Analysis Of The Elements Of Drag In Three-Dimensional Viscous And Inviscid Flows, 2010 California Polytechnic State University, San Luis Obispo
Analysis Of The Elements Of Drag In Three-Dimensional Viscous And Inviscid Flows, Russell M. Cummings, M. B. Giles, G. N. Shrinivas
Russell M. Cummings
This paper examines the analytical, experimental, and computational aspects of tlie determination of the drag acting on an aircraft in flight, with or without powered engines, for subsonic/transonic flow. Using a momentum approach, the drag is represented by an integral over a cross-flow plane at an arbitrary distance behind the aircraft Asymptotic evaluation of tlie integral shows tlie drag can be decomposed into three components corresponding to streamwise vorticity and variations in entropy and stagnation enthalpy. These are shown to be related to tlie established engineering concepts of induced drag, wave drag, profile drag and engine power and efficiency ...
Improved Computational And Experimental Validation Using Different Turbulence Models, 2010 California Polytechnic State University - San Luis Obispo
Improved Computational And Experimental Validation Using Different Turbulence Models, Jay Marcos, David D. Marshall
This paper will explore the methods and techniques necessary to perform a more accurate CFD validation of experimental results. The methods and techniques used will be validated against experimental wind tunnel data of a 2D high lift airfoil with a 3D engine performed by Georgia Tech Research Institute. Preliminary results showed that computational methods over predict the lift and drag coefficient, while still showing very similar trends in CL and CD. To further improve the preliminary results and the predictive capabilities, different turbulence models will be investigated. Results of this validation will assist in determining the appropriate turbulence models, boundary ...
Analytic Confusion Matrix Bounds For Fault Detection And Isolation Using A Sum-Of-Squared-Residuals Approach, 2010 Cleveland State University
Analytic Confusion Matrix Bounds For Fault Detection And Isolation Using A Sum-Of-Squared-Residuals Approach, Daniel J. Simon, Donald L. Simon
Electrical Engineering & Computer Science Faculty Publications
Given a system which can fail in 1 of n different ways, a fault detection and isolation (FDI) algorithm uses sensor data to determine which fault is the most likely to have occurred. The effectiveness of an FDI algorithm can be quantified by a confusion matrix, also called a diagnosis probability matrix, which indicates the probability that each fault is isolated given that each fault has occurred. Confusion matrices are often generated with simulation data, particularly for complex systems. In this paper, we perform FDI using sum-of-squared residuals (SSRs). We assume that the sensor residuals are s-independent and Gaussian, which ...
Ground Support Equipment For Northrop Grumman Massive Heat Transfer Experiment, 2010 California Polytechnic State University - San Luis Obispo
Ground Support Equipment For Northrop Grumman Massive Heat Transfer Experiment, Michael A. Manuel, Christopher J. Sparber, Greg A. Trent
California Polytechnic State University students designed, built, and certified ground support equipment for the Northrop Grumman Massive Heat Transfer Experiment. The Cal Poly design team built the 10000, 20000, and 30000 assemblies to meet Northrop Grumman requirements. The requirements included interface limitations, design load factors, delivery, and testing specifications. The design process consists of requirements generation, conceptual design, preliminary design, design reviews, manufacturing, and certification. The hardware was successfully completed and is used at the Johnson Space and Kennedy Space Center.
Rv-7 N675cp Lean Versus Rich Fuel Mixture Aircraft Performance, 2010 California Polytechnic State University - San Luis Obispo
Rv-7 N675cp Lean Versus Rich Fuel Mixture Aircraft Performance, Edward Spenser Burgos, William Beaman Howe
The purpose of this experiment was to compare the effects of flying with lean mixture versus rich mixture on aircraft performance. This was done by taking data in the RV-7 N675CP aircraft, RV-7A base aircraft that was built by students at California Polytechnic State University of San Luis Obispo. The RV-7 N675CP contains a Lycoming O-360-A 180 HP engine and fully automated flight data acquisition system. Test flight data indicates the aircraft consumes less fuel, has greater engine exhaust gas temperature (EGT), and possibly increases airspeed with a lean fuel mixture.
Interplanetary Gravity Assisted Trajectory Optimizer (Igato), 2010 California Polytechnic State University - San Luis Obispo
Interplanetary Gravity Assisted Trajectory Optimizer (Igato), Jason Bryan
Interplanetary space travel is an extremely complicated endeavor that is severely limited by our current technological advancements. The amount of energy required to transport a spacecraft from one planet to the next, or even further, is extraordinary and in some cases is even impossible given our current propulsive capabilities. Due to these complications, the search for other means of exchanging energy became imperative to future space exploration missions. One particularly powerful method that was discovered, and the most commonly used one, is referred to as planetary gravity assist. In order to plan out multiple gravity assist trajectories, complex and robust ...
Valveless Pulsejet Engine, 2010 California Polytechnic State University - San Luis Obispo
Valveless Pulsejet Engine, Cory William Kerr, James Robert Reynolds
The goal of this project is to build a valveless pulsejet based on the Lady Anne model, known as the Focused Wave Engine VIII Twin Stack. This project has two main goals. The first goal is to design and build the valveless pulsejet. This includes machine work on stainless steel to build the engine, as well as modifying copper tubes to serve as a fuel injection system. The second goal is to build a test stand that allows for accurate data collection of the total thrust being produced by the engine and acts as a fuel injection and ignition system ...
Design, Fabrication, And Testing Of An Automotive Turbocharger-Based Gas Turbine Engine, 2010 California Polytechnic State University - San Luis Obispo
Design, Fabrication, And Testing Of An Automotive Turbocharger-Based Gas Turbine Engine, John Kyle Thoma, Daniel Shehan, Benjamin Naravage, Jacob Melvin
A fully-functioning, self-sustaining gas turbine engine was designed and built. The engine was constructed around a Holset HE351 VGT automobile turbocharger, containing compressor and turbine assemblies on a common shaft. Other components of the engine were either purchased or designed and fabricated in-house. During initial testing of the completed engine, the turbocharger, however, was found to have extensive damage to the internal oil seals, and so the project could not be completed as planned. Instead, the combustor design and fabrication was completed for stand-alone testing. The combustion chamber was designed so that the flame tube could be easily changed out ...
Blended Wing Body Form Factor Code And Model Center Integration, 2010 California Polytechnic State University - San Luis Obispo
Blended Wing Body Form Factor Code And Model Center Integration, Simone (Simo) Alberti
This senior project investigated a method of calculating the form factor of an arbitrarily shaped wing, such as a blended wing body, from its pressure coefficient distribution. A Matlab script was coded and integrated into an existing Model Center tool for blended wing bodies. Model Center allows a VSP model to be analyzed with PMARC, a panel code, to determine the pressure distribution over a wing. The Matlab code can then calculate the form factor and critical Mach number. It was found that the code can accurately model simple planar wings, validated against empirical equations, and is robust for blended ...
Alterations Of The Cal Poly Supersonic Wind Tunnel To Increase Accuracy And Prove The Absence Of Shockwaves, 2010 California Polytechnic State University - San Luis Obispo
Alterations Of The Cal Poly Supersonic Wind Tunnel To Increase Accuracy And Prove The Absence Of Shockwaves, Garrett A. Lovell, Hector A. Gonzalez
The calibration and improvement of the Cal Poly supersonic wind tunnel was performed in order to create a fully functional facility for supersonic testing. While investigating possible shocks present in the wind tunnel, it was discovered that the real concern was not the tunnel but the measurement systems. Both measurement systems, pitot tube and Schlieren, were evaluated and were found to be deficient. The pitot system had so much play in it that it bent backward every time the tunnel was run invalidating the results, and giving false shock data. The Schlieren system was missing one vital component to make ...
Senior Project: Global Position Determination From Observed Relative Position Of Celestial Bodies, 2010 California Polytechnic State University - San Luis Obispo
Senior Project: Global Position Determination From Observed Relative Position Of Celestial Bodies, Michael Holmes
A method was developed to determine the latitude and longitude of an observer based on the observed position of the Moon and several other celestial bodies. The basic principal developed dealt with the proximity of the Moon. Its relative displacement from calculated values was measured using photography by comparison with stars near the Moon. Photographs were taken from a location in San Luis Obispo at Longitude 120°35.9' and Latitude 35°13.3'. The analysis method has determined the location of the observer to a Longitude of 117°43.8'. An additional method located the observer to 36°38 ...
Conceptual Aircraft Hinge Moment Measurement System, 2010 California Polytechnic State University - San Luis Obispo
Conceptual Aircraft Hinge Moment Measurement System, Erin M. Hambrick, Nicole M. Thomason
The Conceptual Aircraft Hinge Moment Measurement System (CAHMMS) was designed, prototyped, and validated to improve hinge moment estimates early in the design process. Validation was performed by integrating CAHMMS with a test wing and conducting wind tunnel tests to compare the expected theoretical, historical, and Computational Fluid Dynamics (CFD) predictions to the experimental results. As CAHMMS is an external measurement system, interference effects at the connection points were investigated. Further studies were undertaken to verify the CFD predictions with the experimental hinge moment measurements. Hinge moment results from the experimental data and the theoretical data closely correlated with less than ...
Analysis Of Curvature Effects On Boundary Layer Separation And Turbulence Model Accuracy For Circulation Control Applications, 2010 California Polytechnic State University - San Luis Obispo
Analysis Of Curvature Effects On Boundary Layer Separation And Turbulence Model Accuracy For Circulation Control Applications, Daniel Wilde
This set of analyses involves flow separation in high curvature regions with special attention to circulation control implementations. Blown flaps of various shapes designed by Rory Golden for use on the AMELIA, or Advanced Model for Extreme Lift and Improved Aeroacoustics, short takeoff vehicle have exhibited flow separation at locations where flap curvature changes. Investigating this problem, its causes, and potential solutions, I have concluded that the separation is equally a function of the flow simulation turbulence model used, and the geometry of the flap itself. Using Gambit version 11.0.1 for grid generation and Fluent version 6.3 ...