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Articles 31 - 60 of 124
Full-Text Articles in Engineering
Two-Stage, High-Altitude Rocket With Internal Skeleton Design Entered In Advance Category Of 7th Esra Irec, Samuel S. Bowman, Kevin J. Byrne, Allen Capatina, Aliki S. Loper-Leddy, Joshua A. Van Schoyck
Two-Stage, High-Altitude Rocket With Internal Skeleton Design Entered In Advance Category Of 7th Esra Irec, Samuel S. Bowman, Kevin J. Byrne, Allen Capatina, Aliki S. Loper-Leddy, Joshua A. Van Schoyck
Aerospace Engineering
A high-altitude, two-stage rocket was designed, built, and entered in the advanced category of the 7th Annual Experimental Sounding Rocket Association (ESRA) Intercollegiate Rocketry Engineering Competition (IREC). The rocket, called AJAKS, featured an internal skeleton made of carbon fiber rods, and a combination of plywood, carbon, and aluminum bulkheads. Loads were driven through the internal structure, with an outer skin tube providing an aerodynamic surface. A unique separation device was developed to ensure proper stage separation. The competition required the rocket to carry a 10-lb payload, which was chosen by the team to consist of an IMU and data …
Registering An Amateur-Built Light Sport Kit Aircraft, Kevin Condron
Registering An Amateur-Built Light Sport Kit Aircraft, Kevin Condron
Aerospace Engineering
No abstract provided.
Flaperon Assembly Manual For Pegastol Aftermarket Wings, Eric Alan Gray
Flaperon Assembly Manual For Pegastol Aftermarket Wings, Eric Alan Gray
Aerospace Engineering
No abstract provided.
Electric Aircraft Propulsion System, Austin J. Doupe
Electric Aircraft Propulsion System, Austin J. Doupe
Aerospace Engineering
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 …
High-Fidelity Low-Thrust Trajectory Determination Research And Analysis, Tyler Hill
High-Fidelity Low-Thrust Trajectory Determination Research And Analysis, Tyler Hill
Aerospace Engineering
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[1] 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 …
Computation Time Comparison Between Matlab And C++ Using Launch Windows, Tyler Andrews
Computation Time Comparison Between Matlab And C++ Using Launch Windows, Tyler Andrews
Aerospace Engineering
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 …
Assembly Of A Passive Slat System For A Ch-701 Kit Aircraft, Jordan Coenen, Spencer Spagnola
Assembly Of A Passive Slat System For A Ch-701 Kit Aircraft, Jordan Coenen, Spencer Spagnola
Aerospace Engineering
No abstract provided.
Low Cost Vacuum Chamber Design For Electromagnetic Railgun Operation, Andrew W. Bothwell, David J. Foster
Low Cost Vacuum Chamber Design For Electromagnetic Railgun Operation, Andrew W. Bothwell, David J. Foster
Aerospace Engineering
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 …
Interstellar Mission To Gliese 581, Brock Schmalzel, Brian Tsoi
Interstellar Mission To Gliese 581, Brock Schmalzel, Brian Tsoi
Aerospace Engineering
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 …
Accelerating Lambert's Problem On The Gpu In Matlab, Nathan Parrish
Accelerating Lambert's Problem On The Gpu In Matlab, Nathan Parrish
Aerospace Engineering
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 …
Development Of A Flight Test Program For A Homebuilt Zenith Stol Ch 701, Reed Danis, Dave Nguyen
Development Of A Flight Test Program For A Homebuilt Zenith Stol Ch 701, Reed Danis, Dave Nguyen
Aerospace Engineering
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 …
Preliminary Design Of A Laboratory Cylindrical Hall-Effect Thruster, Scott Mcgrail, Sam Parker
Preliminary Design Of A Laboratory Cylindrical Hall-Effect Thruster, Scott Mcgrail, Sam Parker
Aerospace Engineering
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 …
Test And Verification Of Vortex Shedding For A 3d Bluff Body, Paul D. Innes, Charles E. Carlson
Test And Verification Of Vortex Shedding For A 3d Bluff Body, Paul D. Innes, Charles E. Carlson
Aerospace Engineering
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 CP 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 CP spikes for the top and bottom of the model without tabs. Trends were observed and compared …
Data Acquisition For Flight Tests Using Handheld Gps And Electronic Flight Instrument System, Christopher Michael Gocha
Data Acquisition For Flight Tests Using Handheld Gps And Electronic Flight Instrument System, Christopher Michael Gocha
Aerospace Engineering
No abstract provided.
Ramjet Fuel System, Kelsey Selin
Instrument Panel Design, Martin Bialy, Amber Carney, Michael Roche
Instrument Panel Design, Martin Bialy, Amber Carney, Michael Roche
Aerospace Engineering
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 …
Empennage Sizing And Aircraft Stability Using Matlab, Ryan C. Struett
Empennage Sizing And Aircraft Stability Using Matlab, Ryan C. Struett
Aerospace Engineering
No abstract provided.
Global Launch Vehicle Selector, Keisuke Suzuki
Global Launch Vehicle Selector, Keisuke Suzuki
Aerospace Engineering
No abstract provided.
The Numerical Open-Source Many-Body Simulator (Noms), Jason Lloyd Daniel, Javen Kyle Foster-O'Neal
The Numerical Open-Source Many-Body Simulator (Noms), Jason Lloyd Daniel, Javen Kyle Foster-O'Neal
Aerospace Engineering
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 …
The Study Of Natural Composite I-Beam In A Three Point Bending Test, Abdel Shabbar
The Study Of Natural Composite I-Beam In A Three Point Bending Test, Abdel Shabbar
Aerospace Engineering
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 …
Comprehensive Matlab Gui For Determining Barycentric Orbital Trajectories, Steve Katzman
Comprehensive Matlab Gui For Determining Barycentric Orbital Trajectories, Steve Katzman
Aerospace Engineering
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 …
A Study On Organic Epoxy And Hemp Composite Plates With An Emphasis On Mechanical And Finite Element Analysis, Alma Melendez
A Study On Organic Epoxy And Hemp Composite Plates With An Emphasis On Mechanical And Finite Element Analysis, Alma Melendez
Aerospace Engineering
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. …
Effect Of Multifunctional Material On The Mechanical Behavior Of Composite Structure Using Finite Element Analysis, Nicholas A. Romonoski
Effect Of Multifunctional Material On The Mechanical Behavior Of Composite Structure Using Finite Element Analysis, Nicholas A. Romonoski
Aerospace Engineering
No abstract provided.
De-Orbiting Upper Stage Rocket Bodies Using A Deployable High Altitude Drag Sail, Robert A. Hawkins Jr., Joseph A. Palomares
De-Orbiting Upper Stage Rocket Bodies Using A Deployable High Altitude Drag Sail, Robert A. Hawkins Jr., Joseph A. Palomares
Aerospace Engineering
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 m2 drag sail, it will de-orbit in …
Degradation Of Solar Cells Due To Arcing In A Vacuum Chamber, Christina Gonzalez
Degradation Of Solar Cells Due To Arcing In A Vacuum Chamber, Christina Gonzalez
Aerospace Engineering
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 …
Development Of A Pyrotechnic Shock Simulation Apparatus For Spacecraft Applications, Joseph Binder, Matthew Mccarty, Chris Rasmussen
Development Of A Pyrotechnic Shock Simulation Apparatus For Spacecraft Applications, Joseph Binder, Matthew Mccarty, Chris Rasmussen
Aerospace Engineering
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 …
Thermal Vacuum Integration For Cal Poly's Space Environments Laboratory, Chelsea Barackman, Steven Jackowski
Thermal Vacuum Integration For Cal Poly's Space Environments Laboratory, Chelsea Barackman, Steven Jackowski
Aerospace Engineering
The purpose of the senior project is to construct a thermal vacuum by utilizing a preexisting vacuum chamber in the Space Environments Lab, and a donated Advanced Thermal Sciences (ATS) chiller. While a thermal vacuum is already available on campus, building one for the Space Environments Lab would grant undergraduates access to the equipment, allowing a much better understanding of testing methods and procedures in use by the aerospace industry. This paper explains the design and analysis of the thermal vacuum (T-VAC) project as well as the operation and procedures required for the ATS chiller and fill/drain tank. The thermal …
Analysis And Testing Of Heat Transfer Through Honeycomb Panels, Daniel D. Nguyen
Analysis And Testing Of Heat Transfer Through Honeycomb Panels, Daniel D. Nguyen
Aerospace Engineering
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 …
Investigating Various Propulsion Systems For An External Attachment For A Controlled-Manual De-Orbit Of The Hubble Space Telescope, Nelson De Guia
Investigating Various Propulsion Systems For An External Attachment For A Controlled-Manual De-Orbit Of The Hubble Space Telescope, Nelson De Guia
Aerospace Engineering
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 …
Electromagnetic Railgun Safety, Sven Ericson
Electromagnetic Railgun Safety, Sven Ericson
Aerospace Engineering
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 …