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Articles 1 - 7 of 7
Full-Text Articles in Engineering
Creation And Analysis Of An Electric And Magnetic Model Of A Micro Ion Thruster, Maxwell Bodnar
Creation And Analysis Of An Electric And Magnetic Model Of A Micro Ion Thruster, Maxwell Bodnar
Aerospace Engineering
This report explores the magnetic and electric fields within the Cal Poly Miniature Xenon Ion (MiXI) Thruster V3 in order to create a comprehensive electric and magnetic model of the plasma chamber to analyze and test the current thruster configurations and changes to the existing thruster. This model is used to analyze the operation and efficiency of the ion thruster and the plasma environment within the plasma chamber. This model explores the ionization and electron collision rates during operation of the thruster to measure the efficiency of the current thruster configuration, also determining the theoretical Isp and thrust of the …
Ramjet Combustion Chamber, Paul Cameron Stone
Ramjet Combustion Chamber, Paul Cameron Stone
Aerospace Engineering
A ramjet combustion chamber is designed and some initial assembly fabrication and test completed as a component of a ramjet graduate project for California Polytechnic State University, San Luis Obispo Supersonic Wind Tunnel. The combustor design is driven by a theoretical model created by a Cal Poly graduate student, Harrison Sykes. Temperature, pressure, and fuel flow will be measured.
Design And Fabrication Of A Ramjet Engine, Clinton C. Humphrey
Design And Fabrication Of A Ramjet Engine, Clinton C. Humphrey
Aerospace Engineering
In this report, the design and fabrication of the inlet to a ramjet engine is described. The inlet utilizes a single ramp and single sided three shock internal compression to slow the airflow from supersonic to subsonic speeds while providing maximum stagnation pressure to the combustor. The optimum angle for the inlet ramp is calculated to be 10° and it decelerates the airflow from Mach 3.3019 to Mach 0.5438. The stagnation pressure increases from 150 psi to 4.67 ksi. The material of the inlet is composed primarily of low carbon mild steel to accommodate the high pressure of the inlet.
Proof Of Concept For Propeller Performance Testing In The Cal Poly Wind Tunnel, Alex N. May, Clayton R. Green, Clinton J. Kirsop, Jason A. Schupp
Proof Of Concept For Propeller Performance Testing In The Cal Poly Wind Tunnel, Alex N. May, Clayton R. Green, Clinton J. Kirsop, Jason A. Schupp
Aerospace Engineering
The goal of this experiment was to execute a proof of concept for a potential propulsion systems laboratory. During the course of this experiment, a data acquisition system was designed, built, and tested in order to collect data from the Cal Poly 3x4 ft draw-down wind tunnel. By operating a brushless outrunner motor and propeller on the sting mount, data was collected for thrust, torque, RPM, current, voltage, and tunnel velocity. By obtaining data for each of these performance metrics, trends were analyzed to confirm the concept and apparatus was functional. The results of the experiment revealed that the concept …
Design And Analysis Of Reusable Nozzles For Cal Poly’S Hybrid Rocket Lab, Cheyne Austin, Jose Vargas
Design And Analysis Of Reusable Nozzles For Cal Poly’S Hybrid Rocket Lab, Cheyne Austin, Jose Vargas
Aerospace Engineering
Two nozzles were designed and constructed for testing in the Cal Poly propulsion laboratory to explore which nozzle was the most capable in producing the most thrust. A 15 degree and 30 degree converging-diverging nozzles were machined and tested. Theory suggest that a bell nozzle would be the most efficient since all of the gasses generated in the combustion chamber are directed and accelerated by the throat leave the nozzle traveling along the thrust axis. All of the momentum of the gasses are directed axially thus resulting in maximum thrust. Thrust should also be produced by the converging-diverging nozzle and …
Nozzle Design For The Supersonic Wind Tunnel Ramjet Attachment, Andrew Michael Carter
Nozzle Design For The Supersonic Wind Tunnel Ramjet Attachment, Andrew Michael Carter
Aerospace Engineering
This document outlines the concept, design, and manufacturing stages of the nozzle section to the Ramjet Attachment. This project is a subsidiary of the thesis, Baseline Performance of Ramjet Engine”, developed by Harrison Sykes. The nozzle geometry is based off of theoretical calculations using Isentropic and Rayleigh line flow relations for a two-dimensional cross section. The nozzle sees an inlet temperature of 953 degrees Fahrenheit, pressure of 28 psi, and a Mach number of 0.356 after the combustion chamber. The nozzle section is a two foot long converging diverging nozzle to choke and accelerate the flow to achieve an exit …
Smore Revision: Ignition And User Interface, Arash Mehrparvar
Smore Revision: Ignition And User Interface, Arash Mehrparvar
Aerospace Engineering
The Static Methanol Oxygen Rocket Engine (SMORE) has undergone several revisions since its inception. This latest revision aimed to increase startup reliability and user safety in the operation of the rocket. The implementation of maintenance procedures, safeguards in the ignition system, as well as construction of a new control box and redesign of the igniter itself have accomplished these goals while keeping costs down and without modifying the current rocket setup. Startup reliability has increased drastically, so long as all other rocket setup procedures are followed properly. 250 subsequent firings of the rocket have proven an igniter reliability of more …