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
Aerospace Engineering
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
Aerospace Engineering
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.[1] 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 in a water …
Interplanetary Gravity Assisted Trajectory Optimizer (Igato),
2010
California Polytechnic State University, San Luis Obispo
Interplanetary Gravity Assisted Trajectory Optimizer (Igato), Jason Bryan
Aerospace Engineering
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 …
Autonomous Control Of The Cal Poly Motion Flight Simulator,
2010
California Polytechnic State University, San Luis Obispo
Autonomous Control Of The Cal Poly Motion Flight Simulator, Andrew M. Anderson
Aerospace Engineering
An autonomous controller for the Cal Poly Motion Flight Simulator was developed such that the simulated Van’s RV-7 flies a standard light aircraft traffic pattern without any human pilot input. First, an autopilot was developed in Simulink to control the aircraft’s altitude, airspeed, and heading independent of each other. The performance of the autopilot has been tested to perform with a response sufficient for precise navigation. A C++ s- function was written as a mission controller that followed a pre-programmed path around a known airport. The aircraft performs a standard left 45 degree entry into the traffic pattern, lands on …
Analysis Of F-104c World's Altitude Record Flight,
2010
California Polytechnic State University, San Luis Obispo
Analysis Of F-104c World's Altitude Record Flight, William J. Day
Aerospace Engineering
No abstract provided.
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
Aerospace Engineering
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 …
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
Aerospace Engineering
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 …
Cal Poly Flight Test Platform For Instrument Development,
2010
California Polytechnic State University, San Luis Obispo
Cal Poly Flight Test Platform For Instrument Development, Kyle Schaller, Ian Muceus, Aaron Ells
Aerospace Engineering
This report summarizes a six month effort to conceptually design, develop, and build an unmanned aerial vehicle to test a boundary layer data system (BLDS) developed by Dr. Russell Westphal and his team of mechanical engineering senior design students. The project is funded by Edwards Air Force Base and the United States Air Force Research Laboratory. During the first Cal Poly quarter of project work, January 4, 2010 to March 18, 2010, the team completed a conceptual and preliminary design. During the second quarter, March 18, 2010 to June 12, 2010, the team completed the construction and initial flight test …
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
Aerospace Engineering
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 …
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
Aerospace Engineering
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 6.3.26 for CFD calculations, …
Hybrid Rocket Motor,
2010
California Polytechnic State University, San Luis Obispo
Hybrid Rocket Motor, Zach Arena, Alexander Athougies, Alden Rodulfo
Aerospace Engineering
This project involves the re-design, manufacturing, and testing of the Cal Poly Space System’s 4th iteration of an M-class 98mm hybrid rocket motor. This motor utilizes hydroxyl-terminated polybutadiene as fuel with liquid nitrous oxide as the oxidizer. Modeling and analysis was conducted on a 12 port self-impinging swirl injector and fuel manufacturing to improve performance. Several hot and cold flow tests were conducted to validate the analysis and predict performance values. Test results included two test fires resulting in an average of 212 lbf of thrust for 6 seconds with an Isp of 160 seconds and an average thrust of …
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
Aerospace Engineering
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.
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
Aerospace Engineering
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°38.7'N Latitude and 114°47.6'W Longitude.
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
Aerospace Engineering
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 …
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
Aerospace Engineering
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.
Matlab® Gui Visualization Of Classical Orbital Elements,
2010
California Polytechnic State University, San Luis Obispo
Matlab® Gui Visualization Of Classical Orbital Elements, Nancy Teresa Cabrera
Aerospace Engineering
The classical orbital elements of an orbit are eccentricity, angular momentum, inclination, right ascension of ascending node, true anomaly, and argument of perigee. These six parameters define an orbit. Using MATLAB® to model a satellite orbiting Earth in three dimensions, a graphical user interface was created to allow a user to manipulate the orbital elements to desired quantities. In doing so, each parameter’s impact on the orbit is visually displayed. This furthers the understanding of how the parameters are linked to the orbit. When the interface is first opened, the default circular orbit has a range of 20,000 kilometers, an …
Valveless Pulsejet Engine,
2010
California Polytechnic State University, San Luis Obispo
Valveless Pulsejet Engine, Cory William Kerr, James Robert Reynolds
Aerospace Engineering
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, Structural Testing, And Numerical Analysis Of A Small Scale Composite Wing,
2010
California Polytechnic State University, San Luis Obispo
Design, Fabrication, Structural Testing, And Numerical Analysis Of A Small Scale Composite Wing, Jacob David Gaunt, Juan Carlos Flores, Vincent Andrew Perry
Aerospace Engineering
A small scale composite wing based on a design found on an experimental aircraft was designed, constructed, and tested dynamically and statically. The wing was constructed similarly to an experimental aircraft wing. The performed static test was intended to produce pure bending. Strain gages were used to measure strains on the wing structure. The strains were converted to stresses to aid in analysis. The static test results suggested that the wing was actually under torsion. Four structural modes were found from the static test. A finite element analysis model was made to compare experimental results to numerical analytical results. The …
Measurement Of Refractive Index Change Of Optical Fiber Core Induced By Femtosecond Laser Scanning,
2010
Missouri University of Science and Technology
Measurement Of Refractive Index Change Of Optical Fiber Core Induced By Femtosecond Laser Scanning, Y. Han, T. Wei, Hai-Lung Tsai, Hai Xiao
Mechanical and Aerospace Engineering Faculty Research & Creative Works
We report a new method to measure the refractive index change in optical fiber core induced by femtosecond (fs) laser exposure. An in-line Fabry-Perot interferometer, serving as the measurement platform, is constructed on a commercial single-mode optical fiber by onestep femtosecond (fs) laser fabrication. A positive refractive index change is observed and measured accurately as the laser pulse energy surpasses the ablation threshold.
Observations Of Temporal Group Delays In Slow-Light Multiple Coupled Photonic Crystal Cavities,
2010
Missouri University of Science and Technology
Observations Of Temporal Group Delays In Slow-Light Multiple Coupled Photonic Crystal Cavities, S. Kocaman, Xiaodong Yang, J. F. Mcmillan, M. B. Yu, D. L. Kwong, C. W. Wong
Mechanical and Aerospace Engineering Faculty Research & Creative Works
We demonstrate temporal group delays in coherently coupled high- Q multicavity photonic crystals, in an all-optical analog to electromagnetically induced transparency. We report deterministic control of the group delay up to 4x the single cavity lifetime in our room-temperature chip. Supported by three-dimensional numerical simulations and theoretical analyses, our multipump beam approach enables control of the multicavity resonances and intercavity phase, in both single and double transparency peaks. The standing-wave wavelength-scale photon localization allows direct scalability for chip-scale optical pulse trapping and coupled-cavity quantum electrodynamics.
