Open Access. Powered by Scholars. Published by Universities.®
- Keyword
-
- Manufacturing (3)
- Matlab (3)
- De-orbit (2)
- Electric (2)
- Orbital debris (2)
-
- Simulation (2)
- Simulator (2)
- Spacecraft (2)
- Zenith (2)
- 100 Year Starship (1)
- Aircraft Stability (1)
- Airplane (1)
- Aluminum (1)
- Arcing (1)
- Assembly Manual (1)
- Attitude Control (1)
- Ballistic impacts (1)
- Barycentric (1)
- Battery (1)
- C++ (1)
- CH 701 (1)
- CPPP (1)
- Cal Poly Pulsed Power (1)
- Cessna (1)
- Composite Structure (1)
- Composites (1)
- Compulsator (1)
- Computer program (1)
- Cuda (1)
- Degradation (1)
- Publication Type
Articles 31 - 45 of 45
Full-Text Articles in Engineering
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 …
The Synergistic Integration Of Computational Fluid Dynamics And Experimental Fluid Dynamics For Ground Effect Aerodynamics Studies, Tj Barber, G Doig, C Beves, I Watson, S Diasinos
The Synergistic Integration Of Computational Fluid Dynamics And Experimental Fluid Dynamics For Ground Effect Aerodynamics Studies, Tj Barber, G Doig, C Beves, I Watson, S Diasinos
Aerospace Engineering
This article highlights the ‘synergistic’ use of experimental fluid dynamics (EFD) and computational fluid dynamics (CFD), where the two sets of simulations are performed concurrently and by the same researcher. In particular, examples from the area of ground effect aerodynamics are discussed, where the major facility used was also designed through a combination of CFD and EFD. Three examples are than outlined, to demonstrate the insight that can be obtained from the integration of CFD and EFD studies. The case studies are the study of dimple flow (to enhance aerodynamic performance), the analysis of a Formula-style front wing and wheel, …
Aerodynamics Of An Aerofoil In Transonic Ground Effect: Methods For Blowdown Wind Tunnel Scale Testing, G. Doig, T. J. Barber, A. J. Neely, D. D. Myre
Aerodynamics Of An Aerofoil In Transonic Ground Effect: Methods For Blowdown Wind Tunnel Scale Testing, G. Doig, T. J. Barber, A. J. Neely, D. D. Myre
Aerospace Engineering
No abstract provided.
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 …
Aerodynamics Of An Aerofoil In Transonic Ground Effect: Numerical Study At Full-Scale Reynolds Numbers, G. Doig, T. J. Barber, A. J. Neely, D. D. Myre
Aerodynamics Of An Aerofoil In Transonic Ground Effect: Numerical Study At Full-Scale Reynolds Numbers, G. Doig, T. J. Barber, A. J. Neely, D. D. Myre
Aerospace Engineering
The potential positive effects of ground proximity on the aerodynamic performance of a wing or aerofoil have long been established, but at transonic speeds the formation of shock waves between the body and the ground plane would have significant consequences. A numerical study of the aerodynamics of an RAE2822 aerofoil section in ground effect flight was conducted at freestream Mach numbers from 0·5 to 0·9, at a range of ground clearances and angles of incidence. It was found that in general the aerofoil's lifting capability was still improved with decreasing ground clearance up until the point at which a lower …
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 …
The Importance And Challenge Of Launch Environment Testing, Christina Diaz
The Importance And Challenge Of Launch Environment Testing, Christina Diaz
Aerospace Engineering
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 …
Aerial Deployable Autonomous Solar Powered Glider, Brandon Groshong, Jacob Ohana
Aerial Deployable Autonomous Solar Powered Glider, Brandon Groshong, Jacob Ohana
Aerospace Engineering
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 …
Feasibility Analysis For Electrically-Powered Hoverboard, Cameron Chan, Jason Cortez, Jay Lopez
Feasibility Analysis For Electrically-Powered Hoverboard, Cameron Chan, Jason Cortez, Jay Lopez
Aerospace Engineering
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 …
Simulation Of Blood Flow And Nanoparticle Transport In A Stenosed Carotid Bifurcation And Pseudo-Arteriole, Graham Doig, Guan H. Yeoh, Victoria Timchenko, Gary Rosengarten, Tracie J. Barber, Sherman C.P. Cheung
Simulation Of Blood Flow And Nanoparticle Transport In A Stenosed Carotid Bifurcation And Pseudo-Arteriole, Graham Doig, Guan H. Yeoh, Victoria Timchenko, Gary Rosengarten, Tracie J. Barber, Sherman C.P. Cheung
Aerospace Engineering
Numerical simulation of flow through a realistic bifurcated carotid artery geometry with a stenosis has been conducted for comparison to experimental measurements. The behaviour of simplified therapeutic nanoparticles in relatively low concentration was observed using a discrete particle approach. The role of size (diameters from 500 nm to 50 nm) in determining particle residence time and the potential for both desirable and undesirable wall interactions was investigated. It was found that mean particle residence time reduced with decreasing particle diameter, and the percentage of particles experiencing one or more wall interactions increased simultaneously. Further simulations were conducted on a scaled-down …
Aircraft Operations Based Mission Requirements, Robert A. Mcdonald
Aircraft Operations Based Mission Requirements, Robert A. Mcdonald
Aerospace Engineering
The mission capabilities of aircraft in the current commercial fleet are a combined result of many factors. The launch customer for each aircraft has a voice in determining the requirements. The manufacturer desires to best position the aircraft in the market considering their own aircraft and their competitors aircraft it will replace and compete with. Consequently, anyone considering the development of an aircraft to compete with or replace an aircraft in-service must do more than simply choose to meet the capabilities of that aircraft. This is especially true when unconventional systems are considered; the fundamental trade-offs for these systems may …