2024-03-29T08:03:25Z
http://digitalcommons.calpoly.edu/do/oai/
oai:digitalcommons.calpoly.edu:aerosp-1000
2011-03-17T16:50:50Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Compression Testing of Composite Laminated Foam under Thermal Loading and with Central Holes
Surano, Dominic
Russo, Jonathan
Leighton, Daniel
Aerospace Engineering Department
BS in Aerospace Engineering
2010-03-17T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Structures and Materials
<p>A study was conducted to investigate the effect of heat on composite sandwich plates, fabricated with the vacuum resin infusion process, with center holes of varying diameters. The study involved conventional notched specimens and notched specimens with shear keys, both of which were subjected to monotonic inplane compression loading. Hole diameter was be varied from one to four inches in one inch increments. Loading rate was applied using the Instron machine at one millimeter per minute. The diameter of the shear key around the holes varied from one inch to four inches in one inch increments. The specimens were placed in a fire chamber at temperatures of 120 and 160 degrees Fahrenheit and tested under compression loading. The specimens at 160 degrees Fahrenheit failed at 20 to 60% of the maximum yielding force as compared to the same specimens at 120 degrees. It was also discovered that the smaller the hole in combination with the largest shear key resulted in the strongest and most reliable specimens.</p>
2011-03-17T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/30
oai:digitalcommons.calpoly.edu:aerosp-1001
2012-05-24T23:29:13Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Satellite Formation Flight Navigation Using the Clohessy-Wiltshire Equations
Kimmich, Anna
Aerospace Engineering Department
BS in Aerospace Engineering
2009-06-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Navigation, Guidance, Control and Dynamics
Clohessy
Wiltshire
satellite
formation
flight
<p>This report presents the design and simulation of a satellite navigation program using Matlab. The program allows any number of independent satellites to navigate in a co-planar cluster formation in a circular orbit with no input besides its location coordinates from a simulated GPS unit and the relative location of other satellites from a simulated on-board sensor. This navigation program uses a potential field-like function to calculate the desired satellite position within the formation. It uses the Clohessy-Wiltshire equations to calculate the impulsive maneuvers needed to achieve and maintain the formation.</p>
2010-03-18T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/66
oai:digitalcommons.calpoly.edu:aerosp-1002
2010-08-02T18:45:37Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
SMORE Phase 2: An Upgrade in Valve Systems & Startup Procedure for A Small Methanol Oxygen Liquid Rocket Engine
Soria, Christian
Aerospace Engineering Department
BS in Aerospace Engineering
2010-03-01T08:00:00Z
Dianne DeTurris, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
Propulsion and Power
liquid rocket engine
rocket engine
propulsion
methanol
oxygen
A Methanol-Oxygen liquid rocket engine was designed and manufactured under the California Polytechnic State University Aerospace Department by students in a graduate level rocket propulsion class. The SMORE, previously known as the KORE, is now in an ongoing testing and developing stage with plans to incorporate it into the aerospace undergraduate propulsion lab. Phase 2 of the liquid rocket engine development is to produce a start-up procedure that will improve the safety due to manual operation and poor ignition conditions. A propane ignition system along with the implementation of electrically operated solenoid valves to control the fuels and oxidizer were the preliminary approach to meeting the objective. However, after testing the propane ignition system it was found to have several shortcomings and instead a simpler re-designed spark igniter became the proven method for ignition without the need of an extra priming fuel, such as propane. Overall the objectives of the second phase of the SMORE were met and proven through live tests.
2010-03-24T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/11
oai:digitalcommons.calpoly.edu:aerosp-1003
2010-08-02T18:58:29Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Experimental Development of Compressor and Turbine Performance Maps for Turbomachinery
Green, Michael W
Aerospace Engineering Department
BS in Aerospace Engineering
2010-04-01T07:00:00Z
Dianne DeTurris, College of Engineering, Aerospace Engineering Department
Propulsion and Power
compressor
turbine
performance
map
turbomachinery
turbojet
Turbomachinery performance maps are used to reveal the on and off design performance of compressors and turbines. These maps plot the component’s pressure ratio versus the corrected flow rate for multiple engine rotor speeds. In this experiment, a Boeing T50-BO-8A converted turbojet engine was operated at a wide variety of rotor speeds with orifice plates of different sizes to vary the flow rate. The corrected flow rate through the turbojet ranged from 1.32 to 2.55 lb/s. The pressure ratios for the compressor and turbine ranged from 2.0 to 4.3 and from 1.7 to 4.3, respectively. The resulting performance maps showed the correct overall trend of increasing flow rate and pressure ratio with higher rotor speeds. However, the individual speed lines were very inconsistent and lacked discernible trends. It was concluded that bench testing the compressor and turbine components is the ideal way to develop the performance maps.
2010-04-27T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/12
oai:digitalcommons.calpoly.edu:aerosp-1004
2010-06-07T15:53:04Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Ground Support Equipment for Northrop Grumman Massive Heat Transfer Experiment
Manuel, Michael A
Sparber, Christopher J
Trent, Greg A
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
David B. Esposto, College of Engineering, Aerospace Engineering Department
Manufacturing
Other Aerospace Engineering
Other Mechanical Engineering
Structures and Materials
Systems Engineering
Ground Support Equipment
GSE
Mechanical Ground Support Equipment
MGSE
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.
2010-05-30T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/2
oai:digitalcommons.calpoly.edu:aerosp-1005
2010-06-07T15:58:12Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Autonomous Control of the Cal Poly Motion Flight Simulator
Anderson, Andrew M
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Navigation, Guidance, Control and Dynamics
UAV
simulation
traffic pattern
autopilot
Van's RV-7
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 the runway, and either choose to stop or perform a touch-and-go based on the pre-programmed command.
2010-06-01T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/1
oai:digitalcommons.calpoly.edu:aerosp-1006
2010-08-02T19:03:12Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Senior Project: Global Position Determination from Observed Relative Position of Celestial Bodies
Holmes, Michael
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
Navigation, Guidance, Control and Dynamics
GPS
Moon
Latitude
Longitude
Right Ascension
Declination
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.
2010-06-07T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/13
oai:digitalcommons.calpoly.edu:aerosp-1007
2010-08-02T19:29:47Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Conceptual Aircraft Hinge Moment Measurement System
Hambrick, Erin M
Thomason, Nicole M
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Mark D. Buchholz, Aerodynamics Engineer, Lockheed Martin Aeronautics
Aerodynamics and Fluid Mechanics
hinge moment
wind tunnel
cfd
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 5% difference, validating the CAHMMS design. Over simplification of boundary layer modeling and mesh generating techniques are attributed to the poor correlation of the analytical data. Understanding of the CAHMMS system and its interactions with the test surface can be further determined through finer mesh generation and more precise boundary layer modeling using the CFD analytical technique.
2010-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/14
oai:digitalcommons.calpoly.edu:aerosp-1008
2010-06-16T15:38:53Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
MATLAB® GUI Visualization of Classical Orbital Elements
Cabrera, Nancy Teresa
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
Orbits
COES
GUI
MATLAB
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 angular momentum of about 133,929 km2/s, an inclination of 45°, a true anomaly of 30°, and right ascension of ascending node and argument of perigee of 0°. This default orbit can easily be changed by sliders and input boxes on the interface. The user-friendly interface allows for anyone to better understand an orbit and its parameters.
2010-06-09T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/3
oai:digitalcommons.calpoly.edu:aerosp-1009
2010-06-16T15:50:00Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
RV-7 N675CP Lean versus Rich Fuel Mixture Aircraft Performance
Burgos, Edward Spenser
Howe, William Beaman
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Aeronautical Vehicles
RV7
lean
rich
fuel mixtures
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.
2010-06-09T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/4
oai:digitalcommons.calpoly.edu:aerosp-1010
2010-08-02T19:39:54Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Analysis of Curvature Effects on Boundary Layer Separation and Turbulence Model Accuracy for Circulation Control Applications
Wilde, Daniel
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
David D. Marshall, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Aeronautical Vehicles
Coanda AMELIA CFD Circulation Control Flaps
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, I have investigated both factors, comparing turbulence models to the experimental data of Monson2 to observe their accuracy in high curvature regions, and designed a set of flap geometries which I subjected to high circulation conditions that exhibit the Coanda effect to compare separation tendencies.
2010-06-11T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/15
oai:digitalcommons.calpoly.edu:aerosp-1011
2010-06-16T15:53:44Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Interplanetary Gravity Assisted Trajectory Optimizer (IGATO)
Bryan, Jason
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
Astrodynamics
Engineering
Navigation, Guidance, Control and Dynamics
orbits
interplanetary optimization
gravity assist
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 computer simulations are required to filter through the continuum of possibilities and select trajectories that optimally satisfy the mission requirements. This paper discusses one such computer simulation which seeks to minimize the propulsive delta v requirements of a spacecraft for a trajectory between two specified planets utilizing a specified number of planetary flybys along the way.
2010-06-11T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/5
oai:digitalcommons.calpoly.edu:aerosp-1012
2010-11-30T01:33:08Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Analysis of a Passive Flow Control Device via Flow Visualization Techniques
Graham, Cheryl R
Huang, Shi (Peter)
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-11T07:00:00Z
Jin Tso, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Karman vortex
drag reduction
passive flow control
flow visualization
bluff body
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 tunnel. The model incorporated a distribution system to dispense the colored dye that allowed visualization of the Karman vortices and related flow characteristics. Two endplates, one with the passive control system and one without, were each tested on the bluff body. Comparison of images captured from the two tests revealed the tab system induced flow characteristics indicative of 3D forcing and drag reduction. Additional investigation of the system performed by varying the angle of attack revealed a decrease in the tab device’s effectiveness as angle to the flow increased. Further experimentation could be done to investigate if modifications exist to improve the performance of the system in conditions not parallel to freestream flow; such a system would expand the potential applications of this passive flow control device in aerodynamic applications.
2010-06-13T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/24
oai:digitalcommons.calpoly.edu:aerosp-1013
2010-08-02T19:46:38Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
MATLAB Structural Analysis Code for String Wing Box Structure
Brown, Sean
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-14T07:00:00Z
Robert McDonald, College of Engineering, Aerospace Engineering Department
Structures and Materials
Human Powered Helicopter
Wing Box
String wing
Finite Element Analysis
Matrix Structural Analysis
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 California Polytechnic State University San Luis Obispo. This code may also be used for the Design Build Fly team at Cal Poly.
2010-06-14T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/16
oai:digitalcommons.calpoly.edu:aerosp-1014
2010-06-16T15:56:27Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Valveless Pulsejet Engine
Kerr, Cory William
Reynolds, James Robert
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Tina Jameson, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
Propulsion and Power
Pulsejet
Pulse jet
valveless
unsteady combustion
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. The pulsejet design was found to produce upwards of 4 lbs of thrust at
optimum fuel to air ratios.
2010-06-14T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/6
oai:digitalcommons.calpoly.edu:aerosp-1015
2010-08-02T19:49:19Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Analysis of F-104C World's Altitude Record Flight
Day, William J
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Robert McDonald, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
F104
aircraft performance
altitude record
2010-06-16T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/17
oai:digitalcommons.calpoly.edu:aerosp-1016
2010-08-02T19:52:49Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Design, Fabrication, Structural Testing, and Numerical Analysis of a Small Scale Composite Wing
Gaunt, Jacob David
Flores, Juan Carlos
Perry, Vincent Andrew
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Aeronautical Vehicles
Mechanics of Materials
Structural Materials
Structures and Materials
Composite
wing
structure
FEA
Finite Element Analysis
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 comparison showed a good correlation with spar stresses, but differences in the experimental and modeled load resulted in no comparison with rib and skin stresses.
2010-06-16T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/18
oai:digitalcommons.calpoly.edu:aerosp-1017
2010-08-02T21:13:32Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Cal Poly Flight Test Platform for Instrument Development
Schaller, Kyle
Muceus, Ian
Ells, Aaron
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Robert McDonald, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Aeronautical Vehicles
Other Aerospace Engineering
UAV
Flight Test
Instrumentation
BLDS
Test Platform
Fast
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 of the UAV.
During the first quarter of work, several different configurations were analyzed. The two most viable were a flying wing with embedded test sections and a conventional configuration with a vertically mounted test model. After considering manufacturing difficulties associated with the flying wing configuration, the traditional configuration was chosen.
During the construction phase of the project, two iterations were built. The first iteration was never flight tested but revealed some needed improvements. The considerable upgrades to the second iteration have developed a flyable UAV available for flight testing.
The final product has a flight weight of 20 pounds 5 ounces and reaches estimated speeds of 60 mph. The initial flight tests reached an endurance time of approximately 5 minutes. However, with an optimization of the power system the aircraft should achieve flight times of roughly 10 minutes.
2010-06-18T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/19
oai:digitalcommons.calpoly.edu:aerosp-1018
2010-06-22T16:20:19Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Design, Fabrication, and Testing of an Automotive Turbocharger-Based Gas Turbine Engine
Thoma, John Kyle
Shehan, Daniel
Naravage, Benjamin
Melvin, Jacob
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Tina Jameson, College of Engineering, Aerospace Engineering Department
Propulsion and Power
Turbine
Turbocharger
Propulsion
Jet
Cycle Analysis
Engine
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 in order to examine the effects of various hole- patterns and fuel-air mixing ratios. Initial testing of the completed combustor assembly showed that the combustion of the propane was not contained within the combustion chamber. Thus the goal of the project was to achieve complete combustion within the combustion chamber while keeping the flame tube structurally sound and the efficiency high. The intent of the project was to supplement the existing propulsion experiments for Cal Poly’s Aero 401 course with a second gas turbine experiment. Due to the setbacks, the project will not be ready to use as a complete lab experiment, however this work-in-progress will be available for future students to learn from and complete, as many of the necessary components have already been designed and fabricated/acquired.
2010-06-21T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/7
oai:digitalcommons.calpoly.edu:aerosp-1019
2010-06-29T16:18:09Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Blended Wing Body Form Factor Code and Model Center Integration
Alberti, Simone (Simo)
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Robert McDonald, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Aeronautical Vehicles
BWB
Model Center
form factor
blended wing body
critical Mach number
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 wing bodies.
2010-06-28T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/8
oai:digitalcommons.calpoly.edu:aerosp-1020
2010-07-01T16:36:01Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Alterations of the Cal Poly Supersonic Wind Tunnel to Increase Accuracy and Prove the Absence of Shockwaves
Lovell, Garrett A
Gonzalez, Hector A
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Dianne DeTurris, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Other Aerospace Engineering
Super Sonic Wind Tunnel
Shock Removal
Shock Detection
Schlieren
Pitot Tube
Shock Visualization
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 it work. By definition the Schlieren was not a Schlieren because it was missing a primary light barrier. Furthermore, once the Schlieren component deficiency was corrected, the architecture of the device impeded use with the tunnel because of vibration limitations. The pitot system was corrected by stiffening the holding bracket and also installing a cross bar that limited horizontal movement. Moreover, the inner converging-diverging section was cleaned, smoothed out, and finally aligned and shaped correctly in order to eliminate and lessen probability of shocks. The experiment was also intended to be used as an instructional tool for undergraduate students at Cal Poly. Students will be able to measure a shock using a 15 degree wedge, a pitot measurement system, and the ability to see a shadowgraph of the shock itself.
2010-06-29T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/9
oai:digitalcommons.calpoly.edu:aerosp-1021
2010-07-07T15:09:59Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
MiXI Thruster Tungsten and Thoriated Tungsten Testing
Miller, Jesse R
Aerospace Engineering Department
BS in Aerospace Engineering
2010-01-01T08:00:00Z
Tina Jameson, College of Engineering, Aerospace Engineering Department
Propulsion and Power
Electric Propulsion
Ion Thruster
MiXI
Tungsten
Thoriated Tungsten
The purpose of this project is to build and evaluate a tungsten filament cathode for the 3-cm Miniature Xenon Ion (MiXI) thruster. The filament is to be used for future tests within the CP 3-cm MiXI and thoriated tungsten is to be examined as a possible alternative. No testing of these filaments was conducted, but the preparatory work has been conducted for future testing.
2010-07-06T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/10
oai:digitalcommons.calpoly.edu:aerosp-1022
2010-08-02T22:30:31Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Initial Design and Simulation of the Attitude Determination and Control System for LightSail-1
Nehrenz, Matthew Thomas
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Jordi Puig-Suari, College of Engineering, Aerospace Engineering Department
This paper discusses the design and simulation of LightSail-1’s attitude determination and control system. LightSail-1 will launch in 2011 and deploy a 32 m2 mylar sail from a 3U CubeSat with the intent of measuring thrust from solar pressure and raising the orbit. The spacecraft will be actively controlled with magnetorquers and a momentum wheel. The various control modes throughout the short mission lifetime include detumble, sun-pointing, and orbit raising. Each one of these modes is simulated in MatLab, and the assumptions and limitations of the MatLab model are discussed. The simulations show that the spacecraft will detumble in 90 minutes after ejection from the P-POD and demonstrate successful sun-pointing within two orbit periods. Orbit raising will require two rapid 90° slew maneuvers every orbit which are accomplished with the momentum wheel.
2010-07-10T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/20
oai:digitalcommons.calpoly.edu:aerosp-1024
2010-10-04T19:33:51Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Hybrid Rocket Motor
Arena, Zach
Athougies, Alexander
Rodulfo, Alden
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Dianne DeTurris, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Aerospace Engineering
Propulsion and Power
Systems Engineering and Multidisciplinary Design Optimization
Hybrid
Hybrid Motor
Hybrid Rocket
HM4
Cal Poly HM4
Cal Poly Hybrid
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 260 lbf of thrust for 6 seconds with an Isp of 200 seconds. Analytical models predicted a thrust of 225 lbf for 6 seconds with an Isp of 180 seconds.
2010-07-16T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/22
oai:digitalcommons.calpoly.edu:aerosp-1025
2010-09-23T22:38:47Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Delamination of Sandwich Composites
Davis, Richard Anthony
Aerospace Engineering Department
BS in Aerospace Engineering
2010-05-01T07:00:00Z
Faysal Kolkailah, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
Engineering
Structures and Materials
Delamination
Sandwich
Composites
Debond
The use of shear keys to help stop or inhibit the face-sheet core delamination of sandwich composite beams under monotonic loading was analyzed in Cal Poly’s structural design lab. The composite beams were treated with the same boundary conditions as the ASTM D5528 double cantilever beam bending in which both faces of the beam remain free; one of the faces would have a debonded side and the other would not. An aluminum tab is attached to the top of the specimens and the load is applied there. Each specimen has piezoelectric sensors that are utilized in the detection of delamination propagation. All the analysis is to be carried out with and without the shear keys. The effects of initial delamlination lengths of 25mm, 50mm, and 75mm were tested with shear keys located at 0.5, 1.0, and 2.0 inches from the start of the delamination. The results found that the closer the shear keys were to the initial delamination, the better they were able to help prevent crack growth and failure. Also, the use of shear keys increased the maximum monotonic load the beam could withstand until it failed compared to samples with no shear keys.
2010-09-21T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/21
oai:digitalcommons.calpoly.edu:aerosp-1026
2010-10-27T21:15:55Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Non-Explosive Actuator Simulator
Costanza, Bryan
Aerospace Engineering Department
BS in Aerospace Engineering
2010-06-01T07:00:00Z
Jordi Puig-Suari, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
CubeSat
Test
Fuse
Actuation
Ground Support Equipment
The CubeSat group at California Polytechnic State University, San Luis Obispo discovered the need for a new piece of ground test equipment. Previous testing of the non-explosive actuator has been very expensive and is not repeatable; two undesirable traits. The analysis of the fuse as well as the design and test of the simulator concept and final article is discussed. The simulator has already seen real use and its entire build and operation cost is much less than the cost of one test of the actual hardware. Performance of the simulator based on burn time and reset time is acceptable while other requirements are not yet fulfilled.
2010-10-05T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/23
oai:digitalcommons.calpoly.edu:aerosp-1027
2011-01-20T17:23:36Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Modeling and Preliminary Finite Element Analysis on the Spun Structure for the CPInterSEP Project
Carpenter, Jason
Cheng, Kelly
Ma, Jeffrey
Pelham, Richard
Povey, Kevin
Aerospace Engineering Department
BS in Aerospace Engineering
2010-12-01T08:00:00Z
David B. Esposto, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
Other Aerospace Engineering
Space Vehicles
Structures and Materials
InterSEP
Finite Element
This paper details the process of modeling and importing the model into FEA for the spun structure of the BS376 spacecraft. Engineering drawings were converted into 3D models using Pro/Engineer and then imported and into Patran for pre-processing of a Finite Element Model. To verify the Finite Element Model, several test cases were set up and solved using Nastran solver. Our simple load cases were found to be in congruence with analytical solution methods validating the finite element model.
2011-01-03T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/25
oai:digitalcommons.calpoly.edu:aerosp-1028
2011-02-18T01:00:42Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Compressor Performance Map Generation and Testing per SAE J1723
Freeman, Jeffrey Lee
Aerospace Engineering Department
BS in Aerospace Engineering
2011-02-01T08:00:00Z
David D. Marshall, College of Engineering, Aerospace Engineering Department
Propulsion and Power
A MATLAB program was written to plot compressor performance maps for a set of test data that was collected in accordance with SAE J1723 at Vortech Engineering, Inc. Paxton Automotive Corp.'s N2500 supercharger was used as a case example for the program, which was carried through from test stand installation to finalized compressor performance map. A sequence was also developed to interpolate the efficiency of the compressor for a given operational setting. The program was shown to be a great improvement from the previously applied technique for accomplishing the same tasks; it is more accurate in plotting the given data, and the time spent performing the process is reduced by approximately seven hours.
2011-02-15T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/26
oai:digitalcommons.calpoly.edu:aerosp-1029
2011-03-03T17:07:39Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Hot Air Balloon Navigation
Blackwell, Dustin
Aerospace Engineering Department
BS in Aerospace Engineering
2010-12-01T08:00:00Z
David D. Marshall, College of Engineering, Aerospace Engineering Department
Navigation, Guidance, Control and Dynamics
Aerospace
Balloon
Navigation
<p>This report describes a program used for navigating a hot air balloon. The program, <em>Balloon_Trip</em>, was written using MATLAB and gives a flight path to follow from a start position to an end position. Balloon_Trip calculates the flight path by taking in wind conditions and then flying through these different winds so as to steer the hot air balloon. The program calculates the flight path by taking into consideration at all times how the wind will propel the balloon while it is rising or falling in elevation. It then takes the most direct and least complicated, if not fastest, route from the starting location to the ending location. All of the flight paths chosen are segmented into five parts, two segments that move the hot air balloon strictly horizontal and three in which the balloon ascends or descends to the specific elevations in which the horizontal movement segments occur.</p>
2011-03-01T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/27
oai:digitalcommons.calpoly.edu:aerosp-1030
2011-03-14T17:39:23Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Two Element Linear Strength Vortex Panel Method
Cox, Clifton A.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-03-01T08:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Panel Method
<p><strong>A linear strength vortex panel method was developed to predict the C<sub>p</sub> and C<sub>l</sub> for a lifting two element airfoil. The linear strength vortex panel method was first validated against thin airfoil theory and experimental data for a single NACA 2412 airfoil. At 2 degrees angle of attack, the linear strength vortex panel method predicted a C<sub>l</sub> of about 0.49. Experimental data and thin airfoil theory gave C<sub>l</sub> estimations of 0.45 and 0.22 respectively. The Matlab code was then modified to accept a two element airfoil. The two key modifications were the separation of the two different sets of wing element panels and the subsequent addition of a second Kutta condition. The linear strength vortex panel method was then used to determine the C<sub>l</sub> and C<sub>p</sub> distribution of a two element wing. The two element wing of study was the rear wing airfoil used on the 2008 Formula SAE car. Using a reference length of 1.43 and an angle of attack of 2 degrees, the panel method predicted a C<sub>l</sub> of 3.98. Improved results can be obtained by using more panels or better geometry resolution around the leading edge and the gap between the two wing elements.</strong></p>
2011-03-08T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/28
oai:digitalcommons.calpoly.edu:aerosp-1031
2011-03-17T16:20:07Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Subwoofer Frequency Response Optimization by Means of Active Control
Dominguez, Luis
Aerospace Engineering Department
BS in Aerospace Engineering
2010-12-01T08:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Controls and Control Theory
Subwoofer
Acoustics
Linkwits
Audio Crossover
Acoustic Active Controls
Audio Filter
<p>Most subwoofer systems have difficulties producing frequencies in the low end of the hearing spectrum due to the added power requirements and instabilities. Active controls can transform the audio signal without changing physical characteristics and ultimately generating a more impressive audio system. A Linkwitz transform crossover was implemented to extend the low end frequency response of a sealed enclosure. A graphical user interface in MATLAB was written to aid in selection of components, driver and enclosure volume. The circuit board was built and integrated with a home theater system inside of a couch and tested with a Real Time Analyzer. The Linkwitz crossover was shown to extend the frequency response, transient response and improve the subwoofer system while reducing the required enclosure volume.</p>
2011-03-15T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/29
oai:digitalcommons.calpoly.edu:aerosp-1032
2011-06-06T17:06:07Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Mapping Galileo's Trajectory
Woods, Mark
Aerospace Engineering Department
BS in Aerospace Engineering
2011-01-01T08:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
astrodynamics
orbital mechanics
Galileo
NASA
JPL
<p>The NASA Galileo mission was mapped out using a patched conics approximation. Galileo launched from Earth, underwent a gravity assist from Venus back to Earth for another gravity assist. Galileo then came back to Earth for one more gravity assist to propel it to Jupiter. A simulation ignoring all perturbations (i.e. third body effects, zonal (harmonics, solar wind, drag) was carried out. The simulation was able to make it to the final Earth flyby before diverging from the actual trajectory. The simulated and actual flyby dates all differed by less than 5 hours, and the simulated and actual flyby altitudes differed by less than 2,000 km.</p>
2011-03-19T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/31
oai:digitalcommons.calpoly.edu:aerosp-1034
2012-06-04T20:01:15Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Development of a Laboratory Experiment to Simulate Upper-Stage Rocket Explosions
Price, Timothy J.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-05-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
Space Vehicles
Debris
Debris Formation
Upper-Stage
Explosion
Spacecraft Environment
<p><strong></strong>This report is a summary of the senior project entitled Development of a Laboratory Experiment to Simulate Upper-Stage Rocket Explosions. The goal of the experiment was to recreate a NASA experiment which used aluminum soft drink cans to approximate the shape of an Ariane third stage rocket. The cans were placed in a vacuum chamber and fired upon with a projectile from a light gas gun. The resulting debris was collected and analyzed allowing several conclusions to be made regarding the behavior or rocket breakups and the formation of space debris. In lieu of a light gas gun, energy drink cans, fitted with a one-way valve from a bicycle inner tube and filled with a hydrogen and oxygen mixture, are detonated with an Estes model rocket motor igniter. The cans were successfully detonated and aluminum debris was formed in a manner consistent with the predictions of the original experiment. This report describes in detail the preliminary experiments and testing leading to the development of the final apparatus and procedure implemented in the Aerospace Engineering Department’s Spacecraft Environment Laboratory. </p>
2011-05-17T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/68
oai:digitalcommons.calpoly.edu:aerosp-1035
2011-06-14T21:49:57Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
An Analysis of Stabilizing 3U CubeSats Using Gravity Gradient Techniques and a Low Power Reaction Wheel
Bender, Erich
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Jordi Puig-Suari, College of Engineering, Aerospace Engineering Department
Astrodynamics
Navigation, Guidance, Control and Dynamics
Space Vehicles
CubeSat
attitude control
gravity gradient
quaternions
spacecraft dynamics
<p><strong>The purpose of this paper is to determine the feasibility of gravity gradient stabilizing a 3U CubeSat and then using a miniature reaction wheel to further increase stability characteristics. This paper also serves as a guide to understanding and utilizing quaternions in attitude control analysis. The analytical results show that using 33 centimeter booms and 400 gram tip masses, a 3U CubeSat will experience a maximum of 6 degrees of angular displacement in yaw and pitch, and less than .5 degrees of angular displacement in the nadir axis. A .120 kilogram miniature reaction wheel developed by Sinclair Interplanetary was introduced into the analysis to understand how it affected stability. Spinning at 3410 RPM and using only 160 milli-Watts of power, the wheel was placed so that it spun around the direction of the velocity vector. The results show that a 3U CubeSat will experience less than .05 degrees of angular displacement in all body axes over many orbital periods.</strong></p>
2011-06-02T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/41
oai:digitalcommons.calpoly.edu:aerosp-1036
2011-12-02T00:43:46Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Decommissioning a Geosynchronous Satellite
Galvan, Anthony D.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Jordi Puig-Suari, College of Engineering, Aerospace Engineering Department
satellite
decommission
end-of-life
geosynchronous
super-synchronous
EOL
<p>Due to factors relating to normal satellite degradation or unexpected anomalous conditions, a satellite will be taken out of commission and placed in a storage mode and eventually powered OFF. Performing end of life (EOL) testing and decommissioning activities require strategic planning. This is to ensure that the satellite can be powered OFF and meet the guidelines to decommission. </p>
2011-06-06T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/56
oai:digitalcommons.calpoly.edu:aerosp-1037
2011-06-08T22:40:01Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Construction of NACA 66-415 NLF Composite Wing for Acoustic Turbulence Testing
Sawyer, Scott
Stewart, Sean
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
William Durgin, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Turbulence
Acoustic
Composite Wing
<p>A design is developed for a Natural Laminar Flow (NLF) wing, to be used at California Polytechnic State University for acoustic turbulence testing. Composite materials are used to produce high-quality surface finishes necessary for laminar flow. A design for the test apparatus is presented and justified. A manufacturing procedure is proposed for the carbon fiber skin, using Vacuum Resin Infusion (VRI). This procedure is tested on a scaled part with satisfactory results; lessons learned are discovered and integrated into the final manufacturing process. The test section has been fit to the Cal Poly wind tunnel, but full implementation has not been completed. Once the proper microphone has been purchased, the final manufacturing to the airfoil can be completed. This will ensure full system integration and completeness.</p>
2011-06-07T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/32
oai:digitalcommons.calpoly.edu:aerosp-1038
2011-06-08T22:47:28Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Electric Aircraft Propulsion Test Rig Design & Fabrication
Mayer, Ryan
Kubicki, Brian
Rodriguez, Bradley
Harris, Austin
Caudle, David
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
William Durgin, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
Propulsion and Power
<p>An electric aircraft propulsion test rig was designed and fabricated to predict thrust, torque and battery discharge profiles for an electric aircraft. The original unit was purchased from ElectraFlyer and included the DC brushless motor, carbon fiber propeller, charger, electronic controller and lithium polymer batteries. Various components were constructed and purchased in order to fabricate the optimal test rig apparatus. This apparatus allows for simultaneous measurement of the torque and thrust of the system through the use of a biaxial sensor. The test rig also measures system voltage and current, which allows the user to determine the discharge profile of the lithium polymer battery pack at various throttle settings.</p>
2011-06-07T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/33
oai:digitalcommons.calpoly.edu:aerosp-1039
2011-06-08T23:37:34Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
The Effects of Damage Arrestment Devices in Composite Plate Sandwiches with Fastener Holes
Anderson, Mark
Hung Choy, Nancy
Jones, Lacey
Kourskaya, Rita
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-08T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Mechanics of Materials
Other Aerospace Engineering
Structural Engineering
Structural Materials
Structures and Materials
Composites
Foam Plate
DAD
Damage Arrestment Device
Fastener Hole
<p>Composite materials such as a carbon fiber are used in a variety of new technologies including aircraft, spacecraft, and motor vehicles. Carbon fiber has a high strength to weight ratio, a key advantage over other material options. This report discusses the use of composite damage arrestment devices (DADs) in composite sandwich panels with a foam core. There are three different curing cycles tested for the DADs: pressure only, vacuum only, and vacuum with 1000 lbs of pressure. Using a Tetrahedron Heat Press to cure the composite specimen and an Instron Machine to perform tensile testing, data was collected for each method. The method that can withstand the highest loads and tensile stresses is the pressure only curing process. Composite sandwich panels were comprised of a FR-6710 polyurethane closed cell foam core and two layers of carbon fiber on each side for the control group. For the specimens with DADs there were two slots milled on each side of the foam and a layer sheet resin was used to bond the surfaces. Compression testing was performed using a jig that had two blots running through the half-inch holes in the specimen. It was found that the specimens that included DADs could withstand 95% higher loads and had a Young’s Modulus of around 85 ksi compared to the control group that was 55 ksi.</p>
2016-06-06T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/34
oai:digitalcommons.calpoly.edu:aerosp-1040
2011-06-08T23:41:06Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Determination of the Surface Boundary Layer Using a Quadrotor
Haviland, Andrew
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-03T07:00:00Z
William Durgin, College of Engineering, Aerospace Engineering Department
Aeronautical Vehicles
Aerospace Engineering
<p><em>Wind velocity data was taken by a quadrotor UAV using accelerometers, gyroscope, and a barometer. Data was taken at different altitudes over a single position to determine the boundary layer at</em><em> the surface of the earth. The data taken was compared to the results from numerical methods to determine if this is a pra</em><em>ctice application for a quadrotor. A few weeks before the test was set to get underway, the quadrotor suffered a very hard crash while testing the GPS and altitude hold function and wasn’t able to completely recover from it. Theoretical results and experiment proposal are covered. </em></p>
2011-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/35
oai:digitalcommons.calpoly.edu:aerosp-1041
2011-06-09T22:13:43Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Scale modeling of Cessna 172
Kim, Chee-woon
Aerospace Engineering Department
BS in Aerospace Engineering
2011-03-20T07:00:00Z
William Durgin, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Scale model
<p>This report describes how the scale-model aircraft can be built when the Reynolds number is out of range for using dynamic similitude method. Due to lack of time and budget for designing an actual model for testing, Cessna 172 was used to calculate the size of the temporary scale-model aircraft. The method that was used for this project was matching aerodynamic coefficients such as drag coefficient or lift coefficient of the prototype and the model. Based on this method, the takeoff distance, landing distance and the rate of climb of the model came out to be 218 ft, 91 ft and 11.1 fpm respectively. Since the performance data of the actual Cessna 172 is already given, calculating those data from the model was avoided.</p>
2011-06-09T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/36
oai:digitalcommons.calpoly.edu:aerosp-1042
2012-06-04T22:34:48Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
An Investigation of Dynamic Soaring and its Applications to the Albatross and RC Sailplanes
Lee, Christopher J.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
William Durgin, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
Albatross
Dynamic Soaring
<p>Dynamic soaring is a technique used by the sea bird the Albatross. This technique allows for the bird to stay in the air for extended periods of time with very little effort. Dynamic soaring utilizes the wind gradient on the surface of the ocean to maintain its airspeed. A similar technique is used by RC glider pilots to achieve high speeds by using the shear wind layer on the leeward side of mountain ridges.</p>
2011-06-09T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/71
oai:digitalcommons.calpoly.edu:aerosp-1043
2011-06-20T21:20:28Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Design and Assembly of a Super Treadmill
Iacob, Simon
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Homayoon Kazerooni
Engineering
Treadmill
<p><strong>This report describes the design and construction of an oversized, ruggedized treadmill built for testing heavy loads. The design permits for speed and slope control, as well as a safety tether and emergency stops. The design description is categorized by related systems. The walking belt is powered by an electric motor, which transfers the mechanical rotation via hubs, a linkage belt and rollers. The floor and surface base are sized and designed for proper operation and clearance. The electronics board provides electric power, speed control, and a powered braking system. Safety features are designed for user protection: guard rails, covers, a gantry crane and tether, and emergency stops. Operation is possible for an incline range of -30° to +30° at 22 increments from the horizontal, and speeds of up to 10 mph with a granularity of 0.01 mph. The larger than usual size and strength allows for extensive usability and testing, for a successful and well-functioning apparatus.</strong></p>
2011-06-10T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/45
oai:digitalcommons.calpoly.edu:aerosp-1045
2011-06-13T17:28:13Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Flight Testing in a Simulation Based Environment
Babka, David W
Aerospace Engineering Department
BS in Aerospace Engineering
2011-01-01T08:00:00Z
William Durgin, College of Engineering, Aerospace Engineering Department
Navigation, Guidance, Control and Dynamics
Other Aerospace Engineering
Flight simulation
X-Plane
Flight Simulator X
Cessna 172
<p>Over the past two decades performance flight testing of full scale aircraft has transferred some of the testing workload to simulation based systems. Flight testing full scale aircraft in the real world environment has always been expensive, especially now with the rise in aviation fuel costs. Additionally, new emerging technologies require extensive testing and doing so in the full scale environment is cost prohibitive. A cheaper alternative is to test systems in a simulation based environment. Not only can aircraft be simulated via a computer, but all the aircrafts systems can be modeled in the simulation. Furthermore, most of the aircraft systems, such as avionics and sensors, can be directly built into the simulation just as they would be on the actual aircraft. The purpose of this report is to review the progression of flight simulation technology, flight testing procedures, and conduct a series of flight tests to compare the data between the actual aircraft in flight with two simulators readily available to the general public. The two simulators considered are X-Plane 9 by Laminar Research and Flight Simulator X from Microsoft. Each simulator uses a different approach to creating the simulated environment. X-Plane uses an engineering process called “Blade Element Theory”, while Microsoft Flight Simulator X uses the more traditional stability derivative method. In order to compare the accuracy of each of these simulations, three flight tests were conducted in each simulator and in the actual aircraft. A Cessna 172SP was the aircraft used in each of the tests. The three tests conducted were flight path stability, stall, and steady turns. Comparing the results, the simulations produced data very similar to that of the actual tests; however, the data did not suggest that either simulation was more accurate than the other. The only distinction between the two simulators that could be made was evident in their user interfaces and ease of operation. Overall, the results obtained in this paper illustrate the effectiveness of the modern flight simulator as an effective testing and design tool. </p>
2011-06-10T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/37
oai:digitalcommons.calpoly.edu:aerosp-1046
2011-06-13T22:04:53Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Composite I-Beam Fabrication and Testing in Response to 14th Annual SAMPE Bridge Competition
Rider, Kodi
Las Piñas, Niño Noel
Mayta, Hans
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-08T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Structures and Materials
Compiste
I-beam
Finite Element Analysis
SAMPE
<p>Composites are a type of material that generally combines two materials yielding mechanical properties that are different than its constituent parts. These constituents are classified as either a fiber or a matrix. The objective of this project is to create a carbon-fiber composite I-beam that meets the specifications of the SAMPE student bridge competition. The I-beam consists of carbon fiber unidirectional and woven laminas, as well as aluminum honeycomb and high density polystyrene foam to stiffen the structure. The bridge contest rules limit the dimensions and weight of the bridge. The cross-section must be within 4 inches x 4 inches with a minimum length of 24 inches, and a maximum weight 600 grams. Theoretical stress and deflection analysis of the bridge was performed using MSC Nastran finite element software. All bridges were manufactured using a wet layup technique and cured under vacuum. Composite bridges were tested using the Instron machine belonging to the Architectural Engineering department at Cal Poly San Luis Obispo. Through analysis and testing, it was determined that web stability was the driving failure mode to design for. Our final bridge failed under 3000 lbf due to buckling of the web directly beneath the applied load. Our first and fourth iterations saw twisting of the flanges because of the lack of stiffness in the flange structure. Our second bridge iteration had the highest strength-to-weight ratio and also took the highest load (3100 lbf) before failing. Based on testing and performance at the SAMPE competition, there are many aspects of this project that can be improved, most importantly through manufacturing techniques. Use of an autoclave as well as using metal molds for curing the beam will dramatically increase load carrying capability.</p>
2011-06-12T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/39
oai:digitalcommons.calpoly.edu:aerosp-1047
2011-06-13T19:28:42Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Analysis of Surface Augmentation of Airfoil Sections via Flow Visualization Techniques
Vento, John Louis
Aerospace Engineering Department
BS in Aerospace Engineering
2011-01-01T08:00:00Z
Bruce Wright, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Aerospace Engineering
surface augmentation
<p>This report details an experiment done to verify the effectiveness of two passive flow control systems on two-dimensional airfoil sections. The flow control was tested on two types of airfoils: a symmetric NACA 0011, intended to represent an airplane in cruise, and a NACA16611, intended to represent an aircraft with flaps extended. Two types of passive systems were employed, a dimple surface augmentation, similar to a golf ball, and a grit system located at 20% chord. Airfoils without either augmentation were tested as a control case. Using a water tunnel and dye to perform flow visualization, the effects of each system were analyzed. Comparison of the image data demonstrated that the surface augmentation dimples aided in delaying the flow separation from the upper surface. The boundary layer separation was measured by using images and locating the point of separation and using the chord line to convert to percent chord separation. The data showed conclusively that the airfoil test section with surface augmentation from 8% chord to the trailing edge had reduced separation throughout the 6 different tests. </p>
2011-06-13T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/38
oai:digitalcommons.calpoly.edu:aerosp-1048
2011-06-14T15:21:24Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
X-51 Composite Airframe
Townshend, Brendon J.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-01-01T08:00:00Z
William Durgin, College of Engineering, Aerospace Engineering Department
Structures and Materials
composite
<p>This paper gives an overview of the progress that has been made in the design build of the X-51. The X-51 is a composite scale replica of a P-51D fuselage integrated with a P-51H wing. Issues with the airframe as well as current action items are discussed, as well as findings so far in preliminary design.</p>
2011-06-13T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/40
oai:digitalcommons.calpoly.edu:aerosp-1049
2011-06-15T19:16:06Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
An Analysis of N-Body Trajectory Propagation
Frees, Emerson, II
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
n-body
orbit
trajectory
stk
<p><strong>Trajectories created with n-body orbit models were propagated in geocentric and interplanetary test cases. The n-body models were created in MATLAB<sup>® </sup>using numerical integration. In the geocentric test case, the n-body codes were compared to a two-body orbit model and to the default HPOP model used in Satellite Tool Kit<sup>®</sup>. The interplanetary test case compared the n-body model to the HORIZONS ephemeris data from JPL and an equation for ephemeris propagation. Both cases used the same initial positions and velocities and were propagated for the same duration. The results of the analysis showed that while n-body models are capable of creating complex orbits that two-body models cannot create, common perturbations such as drag and non-uniform gravity are still necessary to produce accurate trajectory models.</strong></p>
2011-06-15T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/42
oai:digitalcommons.calpoly.edu:aerosp-1050
2012-07-05T15:48:52Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Analysis and Design of an Affordable High Altitude Rocket System
Cooper, Brian
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
Rockoon
Balloon Sounding Rocket
Launch Vehicle
Weather Balloon
low cost
<p>This paper discusses the design of the Rarefied High-Altitude Zenith Experimental Rocket (RHAZER) which is launched at an altitude of 35 kilometers from a weather balloon. The weather balloon is capable of carrying up to 2 kilograms of payload to this altitude, and the rocket can carry a payload of approximately 150 grams to an altitude of at least 80 kilometers and be recovered safely after landing. It is designed to be aerodynamically stable at its launch point, while using fins to spin-stabilize before it enters the low-pressure upper atmosphere. This system has been designed to be used as an educational tool by K-12 schools, so affordability has been the primary driver.</p>
2011-06-15T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/43
oai:digitalcommons.calpoly.edu:aerosp-1051
2011-06-16T17:15:41Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Conical Probe Calibration and Wind Tunnel Data Analysis of the Channeled Centerbody Inlet Experiment
Truong, Samson Siu
Aerospace Engineering Department
BS in Aerospace Engineering
2011-04-01T07:00:00Z
Mike Frederick
Aerodynamics and Fluid Mechanics
Conical
Probe
Calibration
Inlet
F-15
CCIE
<p>For a multi-hole test probe undergoing wind tunnel tests, the resulting data needs to be analyzed for any significant trends. These trends include relating the pressure distributions, the geometric orientation, and the local velocity vector to one another. However, experimental runs always involve some sort of error. As a result, a calibration procedure is required to compensate for this error. For this case, it is the misalignment bias angles resulting from the distortion associated with the angularity of the test probe or the local velocity vector. Through a series of calibration steps presented here, the angular biases are determined and removed from the data sets. By removing the misalignment, smoother pressure distributions contribute to more accurate experimental results, which in turn could be then compared to theoretical and actual in-flight results to derive any similarities. Error analyses will also be performed to verify the accuracy of the calibration error reduction. The resulting calibrated data will be implemented into an in-flight RTF script that will output critical flight parameters during future CCIE experimental test runs. All of these tasks are associated with and in contribution to NASA Dryden Flight Research Center’s F-15B Research Testbed’s Small Business Innovation Research of the Channeled Centerbody Inlet Experiment.</p>
2011-06-15T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/44
oai:digitalcommons.calpoly.edu:aerosp-1053
2011-07-05T19:20:05Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Development and Design of a Hovering Controller for Operation in a Dynamic Asteroid Environment
Georgiades, Nicholas
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Navigation, Guidance, Control and Dynamics
Hovering
Controller
Closed-Loop
Orbit
<p><strong>The project seeks to develop a dynamic model similar to that present near a solar system small body, and to design a controller suggested in other resources that will allow a spacecraft operating in this environment to hover in a fixed location in the relative reference frame of the small body. The paper discusses the derivation of the equations of motion used in the non-linear dynamic model, the design of the controller that will allow the spacecraft to hover, and the development of the control loop that will simulate the spacecraft hovering in the dynamic environment of the asteroid 1999 JU3. A phase plane analysis is conducted to validate the stability of the system, as well as provide a means for adjusting the accuracy to which the controller hovers about the desired set point. The project is successful in all the stated goals, and improvements to the project are discussed.</strong></p>
2011-06-22T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/47
oai:digitalcommons.calpoly.edu:aerosp-1054
2011-06-23T22:47:48Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Thermal Analysis of the CubeSat CP3 Satellite
Friedel, Jonas
McKibbon, Sean
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-07T07:00:00Z
Jordi Puig-Suari, College of Engineering, Aerospace Engineering Department
Space Vehicles
Thermal Analysis
Cubesat
polysat
cp3
<p><strong>Due to inconsistencies found in the on-orbit thermal data from the CubeSat CP3 satellite between 2007 and 2011, further analysis is performed on a larger number of data from August 2010 through April 2011, aiming to find an explanation for the overall increasing measured temperatures and shortening peak periods. Therefore, the satellite power data as well as orbital anomalies are analyzed leading to the conclusion that the satellite was temporarily (January – March 2011) orbiting with significantly increased sun exposure causing the higher temperatures. The shortened temperature peak periods are explained by alternating albedo values as the main influence in temperature changes. Typical thermal coefficients for anodized aluminum of the non-solar cell area of the spacecraft are found by performing basic thermal calculations using the critical temperature data. <br /></strong></p>
2011-06-23T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/46
oai:digitalcommons.calpoly.edu:aerosp-1055
2011-08-11T23:27:06Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
3D CFD on an Open Wheel Race Car Front Wing in Ground Effects
Price, Thomas A.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-07-01T07:00:00Z
Jin Tso, College of Engineering, Aerospace Engineering Department
Aeronautical Vehicles
CFD
computational fluid dynamics
Formula SAE
ground effects
experimental wing
<p><strong>The purpose of the report is to investigate the ability of the Fluent 6.3 k-ε Realizable turbulence model with standard wall functions to model the flow around the front wing of Cal Poly’s 2008 Formula SAE car. The three primary areas of interest are ground effects, the wing wheel interaction, and the wing tip vortices. Fluent was successful at modeling the increase suction from the ground effects, and the upwash due to the wing tip vortices. The results also displayed how the high pressure region in front of the tire propagates forward and interacts with the pressure distribution around the wing. However, Fluent did not predict any separation on the wing in front of the tire, which should be present due to the high pressure region. An experimental wing with pressure taps to record the C</strong><strong>P </strong><strong>distributions around the wing was created and mounted to the car for a track test to validate the computational results. The test has been saved for future work due to mechanical issues with the engine, preventing the Formula SAE team from running the car. The manufacturing process for the wing is also documented, because the Formula SAE team has never made a test wing with pressure ports before. Additionally instead of using traditional foam molds, plaster molds were created for the lay-up in an effort to reduce lead time. The plaster molds took more time to prepare than the foam ones. However time could be saved, because the aerodynamics sub team didn’t have to wait for the CNC router and a technician to cut the mold. The quality and surface finish of the final part was acceptable for a race wing.</strong></p>
2011-07-29T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/49
oai:digitalcommons.calpoly.edu:aerosp-1056
2011-08-11T23:23:03Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Analysis and Design of a Propulsion System Trade Study Tool for a Boeing 376 Series Communications Satellite
Dunk, Kevin
Aerospace Engineering Department
BS in Aerospace Engineering
2011-07-01T07:00:00Z
David B. Esposto, College of Engineering, Aerospace Engineering Department
Propulsion and Power
Cold gas
propulsion
trade study
propulsion sizing
2011-08-05T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/48
oai:digitalcommons.calpoly.edu:aerosp-1057
2011-08-12T00:01:16Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Clifford Algebra Calculations with Representation Theory & an Introduction to Clifford Algebra
Scherling, Alexander I.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-08-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
clifford algebra
representation theory
spin group
<p>The goals of this paper are to provide an introduction to vector, exterior and Clifford algebra and to present a method for performing Clifford algebra calculations efficiently using representation theory. Vectors, exterior algebra and other mathematical and historical foundations of Clifford algebra are introduced. Matrix representations of Clifford algebras are elucidated. The computation of rotations using Clifford representations of spin groups is discussed, and a few of the relevant scientific and engineering applications of the Clifford and exterior algebras are noted throughout.</p>
2011-08-10T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/50
oai:digitalcommons.calpoly.edu:aerosp-1058
2011-09-28T00:40:13Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Design, Manufacturing and Testing of an Environmentally-Green Bipropellant Thruster
Bendoyro, Alex
Sanchez, Gabriel
Stearns, Erin
Takahashi, Phillip
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Tina Jameson, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Aeronautical Vehicles
Other Aerospace Engineering
Propulsion and Power
Space Vehicles
Structures and Materials
Thurster Rocket Biprop Bipropellant spacecraft satellite
<p>This project reviews the design, manufacturing and experimentation process of a green bi-propellant thruster designed to output 5 lbf. The goals were to successfully design, manufacture and test a thruster, while discovering the complications that arise through out the complete design process of a green thruster. The thruster was successfully designed using ideal rocket equations and the design was successfully confirmed using CFD and FEA. Manufacturing of the thruster was fully planned and revealed mild flaws in thruster design. For example some features were not manufacturable to the exact measurements desired. Testing of the engine gave results inconsistent with expected values with a maximum nominal thrust of 2.38 lbf. Measurement errors in thrust and mass flow rates caused calculations of thruster performance, such as ISP, to vary from expected values. Measurement errors are suspected to stem from a combination of incorrect ideal assumptions and test bed design flaws.</p>
2011-08-16T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/52
oai:digitalcommons.calpoly.edu:aerosp-1059
2011-12-07T19:45:47Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Design, Fabrication, and Testing of an Electromagnetic Rail Gun for the repeated testing and simulation of Orbital Debris Impacts
Maniglia, Jeff
Smiroldo, Jordan
Westfall, Alex
Zohar, Guy
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
Astrodynamics
Electromagnetics and Photonics
Other Aerospace Engineering
Power and Energy
Space Vehicles
Structures and Materials
Systems Engineering and Multidisciplinary Design Optimization
railgun
EMRG
Electromagnet Rail Gun
rail gun
<p>An Electromagnetic Railgun (EMRG) was designed, built, and tested, capable of firing a projectile a 1 gram projectile at 650 m/s muzzle velocity. The EMRG utilizes an injector, a high voltage power supply, a capacitor bank, inductors and rails. The injector fires 2300 psig Nitrogen gas into the system to provide an initial velocity. The high voltage power supply charges the capacitor bank. The capacitor bank discharges the electric potential built up through the projectile while inside the rails in order to create the EMRG’s force. The inductors are used to pulse form the capacitor bank in order to get acceleration in more of the EMRG barrel. The barrel consists of two parallel copper bars encased in Garolite-11, Teflon, and Fiberglass. These subsystems all work together for a remote firing of the EMRG during testing. Testing showed that a 0V test resulted in 70 m/s velocity, a 20V test resulted in 165 m/s and 420V test resulted in a minimum of 650 m/s.</p>
2011-09-19T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/58
oai:digitalcommons.calpoly.edu:aerosp-1060
2011-09-28T00:26:36Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Flow Characteristics of the Renovated Cal Poly 3 x 4 ft Subsonic Wind Tunnel
Thomas, Mathew L.
Pandey, Dorian V.
Nguyen, Jason N.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-09-01T07:00:00Z
Jin Tso, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Renovated
Subsonic
Wind
Tunnel
Validation
<p>This paper investigates the flow characteristics of the renovated Cal Poly 3 x 4 ft subsonic wind tunnel. The IFA 300 constant-temperature anemometer along with a cross-plane X-wire dual-sensor probe was used to measure the mean velocity and turbulence intensity of the tunnel flow and part of the turbulent boundary layer at one section of the tunnel. Because of the malfunction of one channel of the IFA 300, only one wire of the dual sensor probe was calibrated for the measurements. The probe was then placed in a streamlined probe holder mounting on the traverse inside the wind tunnel. The turbulent boundary layer thickness was found to be 6 inches. Flow uniformity in the surveyed tunnel section was found to be acceptable with a maximum velocity deviation of 2.5%, and turbulence intensity throughout the vast majority of the tunnel section was found to be less than 0.5%. However, a region of high turbulence intensity (≈2.5%) was found at the top center of the tunnel, which requires further examination.</p>
2011-09-27T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/51
oai:digitalcommons.calpoly.edu:aerosp-1061
2011-10-13T20:39:13Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Comparison of a High Purity Germanium Gamma Ray Spectrometer and a Multidimensional NaI(T1) Scintillation Gamma Ray Spectrometer
Stratton, Greg
Aerospace Engineering Department
BS in Aerospace Engineering
2011-07-01T07:00:00Z
Roger Grismore, College of Science and Mathematics, Physics Department
Electromagnetics and Photonics
Other Aerospace Engineering
Quantum Physics
Systems Engineering and Multidisciplinary Design Optimization
Gamma Ray Spectrometer
<p>This report compares two different gamma ray spectrometers in terms of performance, operation, and apparatus and also investigates the design and integration challenges of using gamma ray spectrometers in space. The first spectrometer is a one-dimensional high purity germanium (HPGe) spectrometer and the second is a multidimensional NaI(Tl) scintillation spectrometer (MGRS). The key results show that the HPGe exhibits 15 to 27 times better energy resolution than the MGRS, but the MGRS is 52 times more sensitive and removes 177 % more of the background radiation.</p>
2011-10-05T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/53
oai:digitalcommons.calpoly.edu:aerosp-1063
2011-11-23T17:49:27Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Study of the Effect of Different Lay-up Methods on the Composite Mechanical Characteristics
Cuevas, Veronica
Salguero, Walter Ely
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Structures and Materials
<p>The purpose of this experiment is to investigate and understand composite structures and the effect of different layup methods on the composite structure, particularly a composite I-beam. One must learn the procedure on how to build the composite I-beam and put it together then build the final composite I-beam and enter the I-beam in the 14<sup>th</sup> Annual Society for the Advancement of Material and Process Engineering (SAMPE) Student Bridge Contest. The competition will be held May 25<sup>th</sup>, 2011 in Long Beach, CA. The I-beam was entered in the competition and placed 4<sup>th</sup> out of 5. The goal for this experiment was to hold a 2,000 lbf , the beam held a force of about 1,000 lbf and a moment of about 10,000 lbf-in. The beams final mass was about 418 grams.</p>
2011-11-21T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/55
oai:digitalcommons.calpoly.edu:aerosp-1064
2011-11-23T17:46:20Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Performance Analysis of a Variable Conductance Heat Pipe
Arreola, Herron
Aerospace Engineering Department
BS in Aerospace Engineering
2011-10-01T07:00:00Z
David B. Esposto, College of Engineering, Aerospace Engineering Department
Space Vehicles
variable conductance heat pipe
heat pipe
thermal engineering
spacecraft design
experimental analysis
heat exchange
<h1>This report examines the analysis of a donated Boeing variable conductance heat pipe with unknown performance characteristics. These characteristics were found through experimental means by utilizing 14 thermocouples attached to various locations on the heat pipe, the heaters and to the insulation. Although the maximum axial heat transport capability could not be determined due to the limited number of strip heaters available, the maximum radial heat flux capability of the heat pipe was found to be 2.46 W/in<sup>2</sup>. The experiment also revealed that increasing the input power decreased the burn out inclination angle and that using a coolant with a lower temperature (ice-water) decreased the wall temperatures of the pipe but not the performance. The active feedback control was also analyzed by attaching a patch heater to the reservoir and increasing the input power from 1 W to 8 W. The feedback system provided temperature control at the evaporator from 45 °C to 74 °C with a 4 °C accuracy while a constant 50 Watt input power was maintained at the strip heaters. The analysis was useful in determining the performance trends of the heat pipe through experimental means and provided the type of information that could verify design predictions or performance claims.</h1>
2011-11-21T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/54
oai:digitalcommons.calpoly.edu:aerosp-1065
2011-12-06T22:56:25Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Radiation in the Space Environment
Hermansen, Sally
Shatts, Jennifer
Aerospace Engineering Department
BS in Aerospace Engineering
2011-12-01T08:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
radiation
space
2011-12-06T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/57
oai:digitalcommons.calpoly.edu:aerosp-1066
2012-01-10T00:59:42Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Wind Tunnel Modeling of Small Electric UAV Power System Performance
Phelps, Nathan R.
Aerospace Engineering Department
BS in Aerospace Engineering
2011-12-01T08:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Propulsion and Power
UAV
electric motors
propellers
windtunnel
<p>This report details the design and construction of a testing apparatus for characterization of small electric aircraft power systems designed for use in the California Polytechnic State University San Luis Obispo Aerospace Engineering department’s subsonic wind tunnel. This apparatus was constructed and implemented with the goal of determining system and component efficiencies of an entire power system using RC Aircraft components as an analog for systems currently in use in the current generation of small electric UAV’s in service with the US Armed Forces. The goal of these experiments was to determine where improvements in the system architecture can be made with a specific goal of extending flight time beyond the current maximum of approximately two hours. It was found that for the test system, the biggest hindrance to optimal performance is the inverse relationship between motor and propeller efficiency. As motor efficiency is increasing, propeller efficiency decreases and the net effect is poor efficiency at all operating points. Additionally, it was found that input voltage has a large effect on overall motor and controller efficiency with a measured change in efficiency of 11% for a constant 10,000 RPM output at voltages ranging from 16.8 to 12 Volts. It was also found that further development is needed to make this apparatus an acceptable solution for precise characterization of actual UAV power systems. The current standard deviation in the power measurement of 28% or is much too large to provide any kind of accurate picture of the actual operating conditions.</p>
2011-12-14T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/60
oai:digitalcommons.calpoly.edu:aerosp-1067
2012-01-03T19:35:56Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Aircraft Longitudinal Control Experiment
Schaff, Dustin
Aerospace Engineering Department
BS in Aerospace Engineering
2011-12-01T08:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Navigation, Guidance, Control and Dynamics
Controls
Servo
Simulink
Sensor
<p>This paper describes the design, fabrication, and analysis of an experiment that demonstrates the stability and control system characteristics of an aircraft constrained at the center of gravity in an air flow field. Given a set of basic requirements, the physical system (including the airframe, wings, tail, and mounted ball bearing) was designed, modeled, and manufactured. With the aircraft placed in front of a fan and allowed to rotate freely with the ball bearing, an angular rate sensor and servo motor to the deflect the elevator may be connected to any computer using an analog/digital Data Acquisition (DAQ) device to send and receive signals needed for the real-time control of the system. Using Simulink and Matlab with the DAQ device, the user may take data on the response of the aircraft and design the control system. The basic open loop input/output responses, system identification, and comparison to a theoretical model are described, and future work will be used to identify the closed loop control characteristics of the experiment.</p>
2011-12-20T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/59
oai:digitalcommons.calpoly.edu:aerosp-1068
2012-01-10T01:03:38Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Hybrid Rocket Based Combined Cycle Test Rig Design, Construction, and Testing
Costa, Mark
Handfelt, Matthew
Aerospace Engineering Department
BS in Aerospace Engineering
2011-06-01T07:00:00Z
Dianne DeTurris, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
Propulsion and Power
2011-12-21T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/61
oai:digitalcommons.calpoly.edu:aerosp-1069
2012-08-06T17:59:23Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Electromagnetic Railgun Safety
Ericson, Sven
Aerospace Engineering Department
BS in Aerospace Engineering
2012-03-01T08:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Systems Engineering and Multidisciplinary Design Optimization
EMRG
CPPP
Cal Poly Pulsed Power
<p><strong>The Cal Poly Electromagnetic Railgun is a system that with the proper precautions can be safely operated. Changes in plugs and boxes insure that the systems cannot be improperly wired, reducing the chances of accidental discharge. By covering exposed wires the system is safe to store as long as the voltage is checked before any maintenance is performed. Updates in procedures remove the possibility of injury to personnel and allow the railgun to be fired repeatedly under similar circumstances. Defined roles for the operators’ decreases confusion and allows people to concentrate on their area during testing. As hardware changes it will be necessary for continued documentation and updating of procedures, as well as continued safety improvements to insure safe and consistent testing. </strong></p>
2012-03-13T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/90
oai:digitalcommons.calpoly.edu:aerosp-1070
2012-03-19T21:54:32Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Investigating Various Propulsion Systems for an External Attachment for a Controlled-Manual De-orbit of the Hubble Space Telescope
de Guia, Nelson
Aerospace Engineering Department
BS in Aerospace Engineering
2012-03-01T08:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
Other Aerospace Engineering
Propulsion and Power
Propulsion systems
de-orbit
Hubble
<p>This reports explains the results for a proposed senior project. This project concerns the Hubble Space Telescope, and exploring the possibility of having an external propulsion attachment for a manual de-orbit. The Hubble Space Telescope was proposed to return to Earth via the Space Shuttle. Although, through the current U.S. Space Administration, the Space Shuttle has been retired before the Hubble Space Telescope was retrieved. By completing this project, the results could provide insight to what type of propulsion would best de-orbit the Hubble upon its retirement. Different propulsion systems were considered to attempt to determine an optimal attachment, varying different specific impulse values, propulsion burn times, preformed !V, and the direction of the thrust impulse. From the calculated results and after conducting a feasibility analysis, it was concluded that a " 450 seconds Isp propulsion system burning for a maximum of 10 minutes proved to be an optimal choice from the simulated cases.</p>
2012-03-14T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/63
oai:digitalcommons.calpoly.edu:aerosp-1071
2012-03-19T21:58:00Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
The Importance and Challenge of Launch Environment Testing
Diaz, Christina
Aerospace Engineering Department
BS in Aerospace Engineering
2012-03-01T08:00:00Z
Andy Pokk (NGAS)
Other Aerospace Engineering
integration
launch
environment
testing
<p>This report discusses the purpose and effect of environmental testing, particularly vibration, shock and acoustic tests, in the aerospace industry. Vibration, shock, and acoustic testing are methods that are used to quantify and analyze the physical phenomenon of the launch environment on a payload or launch vehicle. The importance of innovation in testing and understanding of failures is crucial to a successful spacecraft mission. The advancement and precision of these testing methods is also explored in this report such as the invention of the 6 Degree of Freedom (DoF) vibration table and solutions to data acquisition issues recently discovered in the industry. A detailed overview of how standards particularly MIL- STD-810 have provided uniformity in the industry will also be discussed.</p>
2012-03-15T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/64
oai:digitalcommons.calpoly.edu:aerosp-1072
2012-03-19T21:52:00Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Aerial Deployable Autonomous Solar Powered Glider
Groshong, Brandon
Ohana, Jacob
Aerospace Engineering Department
BS in Aerospace Engineering
2012-03-01T08:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
Electrical and Computer Engineering
uav. glider
solar panel
photovoltaics
servos
battery
<p><strong>Awareness of green solutions to powered flight is a new trend taking the Aerospace Industry by storm. One particular application that shows high promise is that of photovoltaics on small UAV-type aircraft to help extend flight time. The purpose of this report is to document both research and experimentation performed on a small RC aircraft in order to better understand the electrical requirements of such a device. Using that research, speculation on how it can be used to design a mobile Aerial Deployable Autonomous Solar Powered Glider will be performed. Technologies such as CIGS solar cells and Lithium Polymer batteries showed potential as light-weight, high-efficiency sources of power and energy for our system. A theoretical power output of 66.7 W could be produced if the entire .356 m<sup>2</sup> surface of the RC aircraft was covered in CIGS solar cells. As far as experimentation is concerned, it was found that a modest system current of 550 mA and voltage 5.4 V were required to run the RC aircraft servos and receiver at max conditions, using a set of four Ni-Cd batteries. At this current, the glider can last one hour (with margin) using 600mAh Li-Po batteries at that critical 550 mA current. A system power rating of 2.97 W was identified in the RC aircraft, compared to the 39.15 W generated by the solar panels experimented on separately. This led research to focus on the charging requirements as a driver for design rather than the power consumption of the servos. Further research showed that an average voltage of 12V is used for charging most hand-held devices. Ultimately, design created an aircraft that would operate at 14.8V (the voltage of four combined Li-Po batteries in series), being charged by CIGS solar cells.</strong></p>
2012-03-15T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/62
oai:digitalcommons.calpoly.edu:aerosp-1073
2012-04-02T18:56:09Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Feasibility Analysis for Electrically-Powered Hoverboard
Chan, Cameron
Cortez, Jason
Lopez, Jay
Aerospace Engineering Department
BS in Aerospace Engineering
2012-03-01T08:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Manufacturing
Propulsion and Power
Structural Materials
Structures and Materials
Hoverboard
Hover Board
Electrically Powered
Manufacturing
Composites
<p><strong>Composite materials are engineered by combining two or more constituent materials with significantly different physical or chemical properties in such a way that the constituents are still distinguishable, and not fully blended. Due to today’s high rising prices of gasoline and aviation fuel costs, many manufacturers have turned to the use of lightweight composites in their designs due to the advantages of the composite material, which include outstanding strength, excellent durability, high heat resistance, and significant weight reduction that the composite material properties hold. The purpose of this project is to design and construct a composite structure for an electrically-powered hover board designed for human flight. The hover board composite structure consists of three sandwich composite I-beams as the base of the structure where both the flanges and web are composed of fiberglass and a type of foam as the core. The three composite I-beams is essential to our design because as beam theory states, the I-shaped section is a very efficient form for carrying both the bending and shear loads in the plane of the web, which are the two main types of loads that we will encounter. The goals of the system are as follows: 1) the structure of the hover board will be able to withstand all forces and moments created by propulsion system and person; 2) the propulsion system will produce enough thrust to accommodate vertical takeoff for a 170 lb person and achieve a minimum height of three inches; 3) creating a new segment in the aviation and recreational vehicle markets. The goals of this project are very important to achieve as the hover board will be the first of its kind that uses a propulsion system without implementing a skirt. This means that all lift will be created by the four ducted fans in our propulsion system. Once the hover board has been optimized and finalized, it will expand the market of commercially available VTOL systems. At first this technology can be utilized for merely recreation but as time progresses the technology can be expanded to industry. It will replace currently existing cargo movement systems such as forklifts. </strong></p>
2012-03-22T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/65
oai:digitalcommons.calpoly.edu:aerosp-1074
2012-05-31T16:04:22Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Empennage Sizing and Aircraft Stability using Matlab
Struett, Ryan C.
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Navigation, Guidance, Control and Dynamics
Empennage
Aircraft Stability
Matlab
2012-05-23T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/67
oai:digitalcommons.calpoly.edu:aerosp-1075
2012-06-04T22:24:25Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Registering an Amateur-Built Light Sport Kit Aircraft
Condron, Kevin
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kurt Colvin, College of Engineering, Industrial and Manufacturing Engineering Department
Other Aerospace Engineering
2012-06-01T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/69
oai:digitalcommons.calpoly.edu:aerosp-1076
2012-06-04T22:53:50Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
High-Fidelity Low-Thrust Trajectory Determination Research and Analysis
Hill, Tyler
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
Other Aerospace Engineering
Propulsion and Power
low
thrust
electric
propulsion
orbital
mechanics
<p><strong>This document discusses a numerical analysis method for low thrust trajectory propagation known as the proximity quotient or Q-Law. The process uses a Lyapunov feedback control law developed by Petropoulos<sup>[1]</sup> to propagate trajectories of spacecraft by minimizing the user defined function at the target orbit. A simplified propagator is created from the core mechanics of this method in MATLAB and tested in several user defined cases to demonstrate its capabilities. Several anomalies arose in test cases where variations in eccentricity, inclination, right ascension of the ascending node, and argument of perigee were specified. Solutions to these anomalies are discussed and include development of a coasting mechanic and a new method for thruster angle selection.</strong></p>
2012-06-01T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/72
oai:digitalcommons.calpoly.edu:aerosp-1077
2012-06-04T22:30:03Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Analysis and Testing of Heat Transfer through Honeycomb Panels
Nguyen, Daniel D.
Aerospace Engineering Department
BS in Aerospace Engineering
2012-05-01T07:00:00Z
David B. Esposto, College of Engineering, Aerospace Engineering Department
Heat Transfer, Combustion
Other Aerospace Engineering
Structures and Materials
Systems Engineering and Multidisciplinary Design Optimization
Heat Transfer
Honeycomb Panels
Thermocouple
<p>This project attempts to simulate accurately the thermal conductivity of honeycomb panels in the normal direction. Due to the large empty space of the honeycomb core, the thermal radiation mode of heat transfer was modeled along with conduction. Using Newton’s Method to solve for a steady state model of heat moving through the honeycomb panel, the theoretical effective thermal conduction of the honeycomb panel was found, ranging from 1.03 to 1.07 Q/m/K for a heat input of 2.5 W to 11.8 W. An experimental model was designed to test the theoretical results, using a cold plate and a heat plate to find the effective conductance of six samples, each with different colored face sheets or core thicknesses. The experimental data revealed that the analytical results underestimated the conductance, showing a range of difference from 0.31% to 90%. Further analysis regarding the radiation effects is needed to reproduce accurately the effective thermal conductance of the honeycomb panel.</p>
2012-06-04T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/70
oai:digitalcommons.calpoly.edu:aerosp-1078
2012-06-11T22:32:49Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Flaperon Assembly Manual for PegaStol Aftermarket Wings
Gray, Eric Alan
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kurt Colvin, College of Engineering, Industrial and Manufacturing Engineering Department
Other Aerospace Engineering
Structures and Materials
Flaperons
Assembly Manual
Manufacturing
2012-06-06T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/77
oai:digitalcommons.calpoly.edu:aerosp-1079
2012-06-11T22:19:44Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Electric Aircraft Propulsion System
Doupe, Austin J
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Propulsion and Power
Electric
Motor
Propeller
Lithium Polymer Battery
<p><strong>This report specifies the purpose, assembly, operation, and data collection of a testing apparatus to characterize small electric aircraft propulsion systems designed for commercial use. This apparatus was constructed with the goal of determining overall system characteristics and efficiencies. The apparatus was pushed to a safety limit as deemed by advisor John Dunning and the results of the experiment were an output power of 3.2kW (25% of max rated power) and a system efficiency of 58.6%, both of which occurred at 2200 RPM. Currently the apparatus needs improvement. It should have an upgraded structure to mount to (instead of the table in use now), a wind tunnel large enough to fit the system inside (enabling propeller efficiency calculation), and a more robust and less noisy DAQ system. With all those things in place this system could have a major impact on Cal Poly’s Aerospace Department, because as of right now it does not have a single electric aircraft propulsion system. </strong></p>
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/73
oai:digitalcommons.calpoly.edu:aerosp-1080
2012-06-11T22:38:17Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Computation Time Comparison Between Matlab and C++ Using Launch Windows
Andrews, Tyler
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
Time Comparison
Matlab
C++
MEX
Pork Chop Plot
Launch Window
<p>Processing speed between Matlab and C++ was compared by examining launch windows and handling large amounts of data found in pork chop plots. A compilation of code was generated in Matlab to produce the plots and an identical file was created in C++ that was then compiled and run in Matlab to plot the data. This file is known as a MEX-file. This report outlines some of the basics when working with MEX-files and the problems that face users. For Lambert’s solver, multi revolution cases were considered and some pork chop plots of single revolution trajectories were plotted. Three different date grids were plotted with different dimensions to determine the difference in processing speed of the two languages.</p>
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/78
oai:digitalcommons.calpoly.edu:aerosp-1081
2012-06-11T22:22:25Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Assembly of a Passive Slat System for a CH-701 Kit Aircraft
Coenen, Jordan
Spagnola, Spencer
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/86
oai:digitalcommons.calpoly.edu:aerosp-1083
2012-06-11T22:29:16Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Interstellar Mission to Gliese 581
Schmalzel, Brock
Tsoi, Brian
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Space Vehicles
Interstellar
Gliese 581
Nuclear Fusion
Sun Gravitational Lens
100 Year Starship
Exoplanets
<p>This report details a conceptual design for a one-way, interstellar mission, based upon assumed technological advances over the next few hundred years. It addresses the unique challenges associated with an interstellar mission, looking at both developed and theoretical technologies. This report looks specifically at propulsion systems required to reach an exoplanet. In addition, the power, communication, and orbital trajectories are analyzed to see the differences and technological advancements necessary for future missions and the proposed interstellar mission. The destination for the interstellar mission in Gliese 581, a star system located 20.3 light years away and has 5 known planets and an unconfirmed 6<sup>th</sup> planet. There is one known planet that lies in the habitable zone, an area around a star most likely to harbor water or other forms of life, and another known planet on the edge of the habitable zone. The unconfirmed 6<sup>th</sup> planet is thought to be in the middle of the zone and makes Gliese 581 an appealing destination. Nuclear fusion using a <sup>2</sup>H + <sup>3</sup>He reaction is used for the power supply and the propulsion system, with an estimated transit time around two hundred years with two stages of acceleration and one stage of deceleration. The communications system makes use of the sun focal point in order to increase the gain of the transmit antenna and uses two 50 meter dishes on the spacecraft to communicated with the Earth.</p>
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/75
oai:digitalcommons.calpoly.edu:aerosp-1082
2012-06-11T22:45:32Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Preliminary Design of a Laboratory Cylindrical Hall-Effect Thruster
McGrail, Scott
Parker, Sam
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Daniel Wait, College of Engineering, Aerospace Engineering Department
Propulsion and Power
Space Vehicles
Hall Thruster
Space Thruster
Electric Propulsion
Electric Propulsion Design
Space Propulsion
Propulsion Design
<p>A 3-cm cylindrical Hall thruster with permanent magnets was designed and modeled. The goal was to design a Hall thruster for Cal Poly’s propulsion laboratory of similar size and performance as Cal Poly’s MiXI thruster. The design process began with an investigation into the physics of Hall thrusters and selection of certain thruster parameters. The selected parameters were the diameter and depth of the channel, the total power input to the system, the discharge supply voltage, the cathode voltage, and the propellant flow rates to the anode and cathode. These parameters were used to determine the operational characteristics of the thruster which were then used to complete the thruster’s mechanical design. The thrust was estimated to be between 3 and 14 mN, the Isp was estimated to be between 900 s and 2100 s, and the efficiency was estimated to be between 33.3% and 75%.</p>
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/80
oai:digitalcommons.calpoly.edu:aerosp-1084
2012-06-11T22:42:53Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Accelerating Lambert's Problem on the GPU in MATLAB
Parrish, Nathan
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
Astrodynamics
lambert
problem
gpu
cuda
matlab
<p>The challenges and benefits of using the GPU to compute solutions to Lambert’s Problem are discussed. Three algorithms (Universal Variables, Gooding’s algorithm, and Izzo’s algorithm) were adapted for GPU computation directly within MATLAB. The robustness of each algorithm was considered, along with the speed at which it could be computed on each of three computers. All algorithms used were found to be completely robust. Computation time was measured for computation within a for-loop, a parfor-loop, and a call to the MATLAB command ‘arrayfun’ with gpuArray-type inputs. Then, a Universal Variables Lambert’s solver was written in CUDA and compiled for use within MATLAB, where each solution to Lambert’s problem was run as a separate thread. The CUDA-based solver was the fastest of all, solving 1.5x10<sup>6</sup> solutions per second on a laptop GPU and 5.0x10<sup>6</sup> solutions per second on a high-end consumer desktop GPU. The net result is that the Universal Variables algorithm in CUDA runs 76x faster than the same algorithm on the CPU and 3.5x faster than the industry-standard Fortran solver.</p>
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/79
oai:digitalcommons.calpoly.edu:aerosp-1085
2012-06-21T15:39:02Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Development of a Flight Test Program for a Homebuilt Zenith STOL CH 701
Danis, Reed
Nguyen, Dave
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kurt Colvin, College of Engineering, Industrial and Manufacturing Engineering Department
Aeronautical Vehicles
Aerospace Engineering
Kit aircraft
Zenith
Flight Test
CH 701
<p>The objective of this senior project is to prepare a phase I flight test program for a homebuilt Zenith CH 701 kit aircraft. The CH 701 is a small, short takeoff and landing experimental aircraft. A team including several Cal Poly students helped to construct the airframe and avionics of a 701 during the 2011-2012 academic year. The flight test program is necessary for obtaining unrestricted FAA flight certification for the completed aircraft. A set of test flight cards were created to aid in meeting the 25 to 40 hours of required phase I flight testing. These cards include specific instructions for each test as well as notes intended to help the pilot complete the test program safely. The test program outlined by the completed test cards will allow the CH 701 to safely and successfully advance to unrestricted phase II flight testing.</p>
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/84
oai:digitalcommons.calpoly.edu:aerosp-1086
2012-06-21T15:42:23Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Low Cost Vacuum Chamber Design for Electromagnetic Railgun Operation
Bothwell, Andrew W
Foster, David J
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Aerospace Engineering
vacuum chamber
railgun
<p>This report describes the design and fabrication of a low cost vacuum chamber capable of supporting the operation of an electromagnetic railgun. This would be used to simulate the impact of high velocity impacts in space. The vacuum chamber was constructed out of 10in diameter 10ft PVC pipe with a Wye fitting for viewing impacts during testing. The chamber was designed to accommodate a 6.5in X 6.5in X 60in railgun. The vacuum chamber feedthroughs were designed to be able to carry 1-2Mamps at 8kV to the railgun. The vacuum chamber is capable of reaching 50 Torr and remaining under 100 Torr for 11 minutes. The final cost of the chamber was $1325.</p>
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/85
oai:digitalcommons.calpoly.edu:aerosp-1087
2012-06-11T22:31:00Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Global Launch Vehicle Selector
Suzuki, Keisuke
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Daniel Wait, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
GUI
computer program
launch vehicle
global
rocket
2012-06-08T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/76
oai:digitalcommons.calpoly.edu:aerosp-1088
2012-06-21T15:45:09Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Data Acquisition for Flight Tests using Handheld GPS and Electronic Flight Instrument System
Gocha, Christopher Michael
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Daniel J. Biezad, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
2012-06-11T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/83
oai:digitalcommons.calpoly.edu:aerosp-1089
2012-06-11T22:25:24Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Test and Verification of Vortex Shedding for a 3D bluff body
Innes, Paul D
Carlson, Charles E
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Jin Tso, College of Engineering, Aerospace Engineering Department
Aerodynamics and Fluid Mechanics
Aerospace Engineering
vortex
<p>Testing of a 3D bluff body with and without end plate tabs was performed in the California Polytechnic State University 3x4 ft low speed wind tunnel. The C<sub>P</sub> values were obtained for the test case with no end plate tabs for speeds of 10, 15, 20, and 30 m/s. It was observed that stronger vortex shedding ocured at the higher speed test cases. The model was shimmed to be at approximately 5° angle of attack in order to obtain symmetrical negative C<sub>P</sub> spikes for the top and bottom of the model without tabs. Trends were observed and compared to trends previously noted in Jarred Pinn’s thesis. The baseplate was replaced with one that contained tabs along the spanwise direction, and it was observed that the vortex shedding was eliminated with the addition of the base plate tabs. The data obtained confirmed previous trends seen that tabs resulted in reduced drag and elimination of vortex shedding at the top and bottom of the model base.</p>
2012-06-11T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/74
oai:digitalcommons.calpoly.edu:aerosp-1090
2012-06-19T21:14:26Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Instrument Panel Design
Bialy, Martin
Carney, Amber
Roche, Michael
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kurt Colvin, College of Engineering, Industrial and Manufacturing Engineering Department
Aeronautical Vehicles
Instrument
Panel
<p>This project focused on the design and implementation of an Electronic Flight Instrument System for a home built experimental aircraft known as a CH-701. Older aircraft use manual gauges and dials based on varying internal instruments such as gyro’s and the like but many of these traditional instruments to a singular GUI displaying multiple instruments data at one time. These devices are aimed at helping the pilot stay more alert and aware when flying between automatic warnings when in dangerous flying conditions / configurations as well as simplifying the instrument panel to only display what is absolutely necessary. These programs help with reaction time and response and will improve the overall safety of the flight for the pilot, passengers and ground civilians alike.</p>
2012-06-11T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/81
oai:digitalcommons.calpoly.edu:aerosp-1091
2012-06-21T15:30:22Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Ramjet Fuel System
Selin, Kelsey
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Daniel Wait, College of Engineering, Aerospace Engineering Department
Propulsion and Power
Ramjet
Fuel System
2012-06-12T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/82
oai:digitalcommons.calpoly.edu:aerosp-1092
2012-06-27T15:29:23Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Degradation of Solar Cells Due to Arcing in a Vacuum Chamber
Gonzalez, Christina
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Other Aerospace Engineering
Arcing
Solar Cells
Vacuum
Degradation
<p>This report summarizes the senior project entitled Degradation of Solar Cells Due to Arcing in a Vacuum Chamber. The goal of this experiment was to show electrical and physical degradation of silicon solar cells in a vacuum chamber. The cells were characterized and then placed in a vacuum chamber. Under vacuum, a potential was created to induce arcing to the cell. The cell was characterized again after arcing to determine the change in efficiency. This document details the process for designing the circuit to create the arcing, and the different setups used to degrade the cells electrically and physically. It also describes the final setups to be used in the lab write-up for the Aerospace Engineering Department’s Spacecraft Environment Laboratory.</p>
2012-06-27T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/87
oai:digitalcommons.calpoly.edu:aerosp-1093
2012-07-09T17:09:40Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
The Study of Natural Composite I-Beam in a Three Point Bending Test
Shabbar, Abdel
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Structures and Materials
Natural Composite testing SAMPE I-beam
<p>The objective of this experiment is to conduct a series of unidirectional tensile test on several samples of natural occurring plant fibers. Among the materials tested, hemp has proven to be the most promising candidate as the base material in creating an all-natural composite I-Beam. This I-Beam will be entered into the annual SAMPE 2012 competition to compete against other schools and universities nationwide. These I-Beams will undergo a three point bending test, and must withstand the greatest load whilst remaining in the parameters set by SAMPE. This I-Beam will go on to take third place internationally. In addition, the properties of hemp composites will be further investigated by creating the same I-Beam, but introducing a small fracture to the underside in order to observe how the composite interacts in the presence of fracture.</p>
2012-06-29T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/88
oai:digitalcommons.calpoly.edu:aerosp-1094
2012-07-18T23:25:57Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Comprehensive Matlab GUI for Determining Barycentric Orbital Trajectories
Katzman, Steve
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
Navigation, Guidance, Control and Dynamics
Barycentric
Matlab GUI
Lagrange Points
Free Return Trajectory
<p>When a 3-body gravitational system is modeled using a rotating coordinate frame, interesting applications become apparent. This frame, otherwise known as a barycentric coordinate system, rotates about the system’s center of mass. Five unique points known as Lagrange points rotate with the system and have numerous applications for spacecraft operations. The goal of the Matlab GUI was to allow easy manipulation of trajectories in a barycentric coordinate system to achieve one of two end goals: a free-return trajectory or a Lagrange point rendezvous. Through graphical user input and an iterative solver, the GUI is capable of calculating and optimizing both of these trajectory types for all of our solar system’s planets. Its inputs are inertial state vectors, a date and time, and the number of propagation days. The user can then graphically manipulate the resulting trajectories by increasing the spacecraft velocity and propagation start time. It outputs the resulting ΔV vectors and magnitudes as well as a graphical representation of the desired orbital path.</p>
2012-07-12T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/89
oai:digitalcommons.calpoly.edu:aerosp-1095
2012-08-06T18:03:25Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Control Experiment: Model Helicopter
Lattanzi, Matthew D.
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Eric Mehiel, College of Engineering, Aerospace Engineering Department
<p>This report describes the design and analysis of a control experiment to be implemented in the AERO 320 curriculum. The purpose of the experiment is to give the students hands-on experience working with a control system. In addition, the experiment aims to demonstrate the effect a proportional, integral, derivative (PID) controller has on a control system. The system to be controlled is a model helicopter, constrained to vertical motion. The physical system was built using radio controlled (RC) components, off-the-shelf products, and custom designed parts. The system was tested using an RC transmitter and receiver to manually control the height of the model. A Simulink model with PID controller and simplified plant model was developed and analyzed. A Routh-Hurwitz tabulation was conducted to determine the range of controller gains that would stabilize the system. The gains were varied to determine the effect on the step response and Bode diagram for the helicopter model. The results showed that the changing gain values did not affect the phase margin or gain crossover frequency of the system. Future improvements to the physical system and Simulink model are covered in detail at the end of the report with end goal of testing the system closed loop.</p>
2012-07-18T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/91
oai:digitalcommons.calpoly.edu:aerosp-1096
2012-09-12T21:08:02Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
The Numerical Open-Source Many-Body Simulator (NOMS)
Daniel, Jason Lloyd
Foster-O'Neal, Javen Kyle
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
David D. Marshall, College of Engineering, Aerospace Engineering Department
Astrodynamics
orbit
simulator
galaxy
n-body
gravity
integrator
<p>This paper outlines the setup and creation of an object-oriented N-body simulator as part of a continued project to explore physical phenomenon and human-computer natural interaction technologies. The tools and processes required to build an N-body simulator are also included. Several integrators were evaluated based on their ability to maintain system energy The 2nd order integrator Verlet and 3rd order integrator Hermite algorithms had the greatest accuracy to model large-scale N-body dynamics for their given computation time. Other algorithms required significantly shorter time steps to achieve similar short-term accuracy. At present, NOMS can reasonably simulate 10,000 particles at less than one minute per iteration.</p>
2012-09-10T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/92
oai:digitalcommons.calpoly.edu:aerosp-1097
2012-09-25T22:28:33Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Performance Effects of Damage Arrestment Devices on Sandwich Composite Beams under Monotonic Loading
Wood, Yvette Vanessa
Aerospace Engineering Department
BS in Aerospace Engineering
2012-09-01T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Structures and Materials
<p>Face-core delamination has become a subject matter in the Aerospace industry, as it can lead to early failure. In this study, sandwich composite beams are tested initially with no delamination to obtain the ultimate strength. A second case of delamination in the center of the beam in initialized to verify a decrease in ultimate strength. This experiment investigates the performance effects of the addition of Damage Arrestment Devices (DADs), in composite sandwich beams. The performance criterion is measured by strength in flexural loading test. The objective of this project is to verify an increase in the strength and performance with the addition of DADs in a sandwich composite. Theoretical and experimental results confirmed that adding damage arrestment devices into the sandwich composite material increases the loading capability of the structure.</p>
2012-09-17T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/95
oai:digitalcommons.calpoly.edu:aerosp-1098
2012-09-25T21:47:58Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Development of a Pyrotechnic Shock Simulation Apparatus for Spacecraft Applications
Binder, Joseph
McCarty, Matthew
Rasmussen, Chris
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
David B. Esposto, College of Engineering, Aerospace Engineering Department
Acoustics, Dynamics, and Controls
Aeronautical Vehicles
Aerospace Engineering
Engineering Physics
Mechanical Engineering
Navigation, Guidance, Control and Dynamics
Other Aerospace Engineering
Other Mechanical Engineering
Other Physics
Space Vehicles
Structures and Materials
shock
pyroshock
pyrotechnic
simulation
spacecraft
impulse
<p>This report details the research, design, construction, and testing of a pyrotechnic shock simulation apparatus for spacecraft applications. The apparatus was developed to be used in the Space Environments Lab at California Polytechnic State University. It will be used for testing spacecraft components with dimensions up to 24”x12”x12” as well as CubeSats. Additionally, it may be used as an instructional or demonstrational tool in the Aerospace Department’s space environments course. The apparatus functions by way of mechanical impact of an approximately 20 lb stainless steel swinging hammer. Tests were performed to verify the simulator’s functionality. Suggestions for improvement and further progress are also given.</p>
2012-09-24T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/93
oai:digitalcommons.calpoly.edu:aerosp-1099
2012-09-25T21:50:55Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
A Study on Organic Epoxy and Hemp Composite Plates with an Emphasis on Mechanical and Finite Element Analysis
Melendez, Alma
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Aerospace Engineering
Structures and Materials
natural fiber hemp composites
hemp composite plates
organic epoxy
<p>Several vibration and tensile tests were conducted for four natural fiber hemp composites in order to observe its behavior and acquire the material properties of hemp. Two plates were made on the Cal Poly press table, while the other two plates were made on the Cal Poly vacuum table. All four plates are made of 100% hemp under three different types of weave. The first plate is called CTPT-12, has a thickness of 0.053 inches, and was made on the press table. The second plate is called CTL4 with a thickness of 0.152 inches and made on the press table. The third plate is called HL-10 with a thickness of 0.2145 inches, and made on the vacuum table. The fourth plate is called CTPT-12 with a thickness of 0.264 inches and made on the vacuum table. A second portion of the project was performed to further study the behavior of hemp composites. Several hemp plates with dimensions of 1.5 inch by 6 inch were made. These plates were manufactured in the vacuum table with four layers of CTPT-12 material and a 1 inch by 1.5 inch delamination. The results indicated a maximum stress of 118280 psi and a maximum displacement of 2 inches from end to end. Each plate was made with organic epoxy under a curing cycle that lasted about a day at a temperature of 150° F. Each plate had a different material property due to its different weave and manufacturing process.The plate that resisted the highest force and the highest Young’s Modulus was the fourth plate with 704 lbf and 937 ksi, respectively. Plate 2 resisted the least with a force of 278 lbf and a Young’s Modulus of 554 ksi. Plate 3 had the lowest Young’s Modulus of 513 ksi with a force of 379 lbf. The vibration sweep ranged from 5 Hz to 1000 Hz with varying control amplitude throughout the run. The results indicated that there were significant differences between the four plates. The first plate had the highest natural frequency of 69.93 Hz at a distance of 4 inches from the surface of the aluminum blocks holding the plate for the vibration test. Plate 2 had the lowest frequency of 5 Hz when the accelerometer was placed 8 inches from the surface of the aluminum blocks. The experiment concluded that the experimental values and the finite element analysis had some similar results.</p>
2012-09-24T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/94
oai:digitalcommons.calpoly.edu:aerosp-1100
2012-11-29T21:40:19Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Validation of the Ballistic Limit Equation for Monolithic Aluminum Shielding at Geostationary Orbital Debris Impact Velocity
Holladay, Brandon
Aerospace Engineering Department
BS in Aerospace Engineering
2012-10-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Space Vehicles
orbital debris
shielding
ballistic impacts
geostationary orbit
monolithic shielding
Whipple shield
mesh bumper
Electromagnetic railgun
<p>The Cal Poly Electro Magnetic Rail Gun was used to eject a 0.370 gram, rectangular aluminum projectile towards a 1/16 inch monolithic aluminum plate at a speed of 280 ± 50 m/s. The resulting impact left a large attached spall on the back of the shielding. The impact damage was compared to an industry ballistic limit equation for a spherical aluminum projectile of similar diameter and was shown to have slightly less damage than the expected results.</p>
<p>In addition, an aluminum mesh double bumper shield was fired upon in order to verify its higher protection per aerial density as well as its higher projectile break-up ability. An impact at 459 ± 50 m/s resulted in superior shielding performance over an aluminum monolithic shield of equivalent areal density, based on the ballistic limit equation; however projectile break up did not occur. A minimum mass savings of 23% was realized using the mesh double bumper shield. Furthermore, when an additional aluminum bumper was placed in front of the mesh bumper, even greater ballistic protection was achieved with a minimum mass savings of over 65%.</p>
<h1> </h1>
2012-10-12T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/98
oai:digitalcommons.calpoly.edu:aerosp-1101
2012-11-29T21:38:00Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Three-Axis Stabilized Earth Orbiting Spacecraft Simulator
Ma, Alan F.
Dominikovic, Nikola N.
Aerospace Engineering Department
BS in Aerospace Engineering
2012-10-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
Navigation, Guidance, Control and Dynamics
Spacecraft Simulator
Simulator
Attitude Control
Orbit Propagation
<p>This report details the method and results of the program created for simulating an Earth orbiting spacecraft with control actuators and orbital perturbations. The control actuators modeled are reaction thrusters, reaction/momentum wheels, and control moment gyros (CMG). The perturbations modeled were gravity gradient, electromagnetic torques, solar radiation pressure, gravity gradients, third-body effects, Earth oblateness and atmospheric drag. This simulation allows for satellite control in all 6 degrees of freedom for any Earth orbiting spacecraft. Assumptions include rigid body dynamics, no sensor noise, constant spacecraft cross-sectional area, constant coefficient of drag and reflectivity, ignoring the effects due to the moon, moment of inertia doesn’t change with a change in mass, and reaction thrusters only produce torque. The results from test trials showed reasonable numbers and system behavior.</p>
2012-10-16T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/97
oai:digitalcommons.calpoly.edu:aerosp-1102
2012-11-13T23:54:55Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Effect of Multifunctional Material on the Mechanical Behavior of Composite Structure Using Finite Element Analysis
Romonoski, Nicholas A
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Eltahry Elghandour, College of Engineering, Mechanical Engineering Department
Structures and Materials
2017-10-20T07:00:00Z
https://digitalcommons.calpoly.edu/aerosp/96
oai:digitalcommons.calpoly.edu:aerosp-1103
2012-12-12T20:52:48Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
De-Orbiting Upper Stage Rocket Bodies Using a Deployable High Altitude Drag Sail
Hawkins, Robert A, Jr.
Palomares, Joseph A
Aerospace Engineering Department
BS in Aerospace Engineering
2012-06-01T07:00:00Z
Kira Abercromby, College of Engineering, Aerospace Engineering Department
Astrodynamics
Other Aerospace Engineering
Propulsion and Power
Space Vehicles
orbital debris
drag sail
drag
de-orbit
rocket body
rocket bodies
spacecraft
NASA Procedural Requirements for Limiting Orbital Debris
<p>This report examines the effectiveness of a drag sail to de-orbit upper stage rocket bodies. Many other perturbations contribute to the de-orbiting of these rocket bodies, and these perturbations will also be discussed briefly. This paper will show the length of time needed to force the altitudes of various launch vehicle stages with varying drag area sizes to less than 100 km. The upper stage of the Delta IV launch vehicle in an orbit with an altitude of 500 km will naturally de-orbit in 720 days but when equipped with a 20 m<sup>2</sup> drag sail, it will de-orbit in just 510 days. For this particular example the 29% reduction in de-orbit time is very significant. Multiple examples will be displayed in this report to demonstrate the effectiveness of such a drag sail.</p>
2012-12-04T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/99
oai:digitalcommons.calpoly.edu:aerosp-1104
2012-12-12T20:55:34Z
publication:research
publication:students
publication:aerosp
publication:seniorprojects
Manufacturing Processes in an All-aluminum Airframe
McDougall, Stewart
Aerospace Engineering Department
BS in Aerospace Engineering
2012-11-01T07:00:00Z
Kurt Colvin, College of Engineering, Industrial and Manufacturing Engineering Department
Structures and Materials
aluminum
manufacturing
airplane
flaps
Cessna
Zenith
<p>One often overlooked aspect to building an aircraft is the manufacturing process used to put it into production. This may be a major contributor to acquisition cost and requires a large amount of money to implement. Once all the tooling has been purchased, one of the greatest costs is labor. The experience of building an all-aluminum aircraft shows that the production process is one which may be done in many different ways. Minimizing the assembly time is important for aircraft manufacturers and one of the best ways to do that is on the assembly line itself. Specific practices in the manufacturing process can speed up production, and this paper shows some practical examples of that.</p>
2012-12-05T08:00:00Z
https://digitalcommons.calpoly.edu/aerosp/100
1104796/qualified-dublin-core/100//