ASU Electronic Theses and Dissertations
This collection includes most of the ASU Theses and Dissertations from 2011 to present. ASU Theses and Dissertations are available in downloadable PDF format; however, a small percentage of items are under embargo. Information about the dissertations/theses includes degree information, committee members, an abstract, supporting data or media.
In addition to the electronic theses found in the ASU Digital Repository, ASU Theses and Dissertations can be found in the ASU Library Catalog.
Dissertations and Theses granted by Arizona State University are archived and made available through a joint effort of the ASU Graduate College and the ASU Libraries. For more information or questions about this collection contact or visit the Digital Repository ETD Library Guide or contact the ASU Graduate College at email@example.com.
- 3 English
- 3 Public
This thesis gives a detailed design process for a pulsed type thruster. The thrust stand designed in this paper is for a Pulsed Plasma Thruster built by Sun Devil Satellite Laboratory, a student organization at Arizona State University. The thrust stand uses a torsional beam rotating to record displacement. This information, along with impulse-momentum theorem is applied to find the impulse bit of the thruster, which varies largely from other designs which focus on using the natural dynamics their fixtures. The target impulse to record on this fixture was estimated to be 275 μN-s of impulse. Through calibration and experimentation, …
- Verbin, Andrew Joseph, Takahashi, Timothy T, White, Daniel B, et al.
- Created Date
The aerospike nozzle belongs to the class of altitude compensating nozzles making it a strong candidate for Space Shuttle Main Engines. Owing to their higher efficiency compared to conventional bell nozzles, the aerospike nozzles are being studied extensively and are being used for many Single State to Orbit (SSTO) designs. A rocket engine nozzle with altitude compensation, such as the aerospike, consumes less fuel than a rocket engine with a bell nozzle. Aerospike nozzles are huge and are often difficult to construct and have to be truncated in order to make them feasible for application in a rocket propulsion system. …
- Nagarajan, Venkatraman, White, Daniel B, Dahm, Werner, et al.
- Created Date
Two methods of improving the life and efficiency of the Pulsed Inductive Thruster (PIT) have been investigated. The first is a trade study of available switches to determine the best device to implement in the PIT design. The second is the design of a coil to improve coupling between the accelerator coil and the plasma. Experiments were done with both permanent and electromagnets to investigate the feasibility of implementing a modified Halbach array within the PIT to promote better plasma coupling and decrease the unused space within the thruster. This array proved to promote more complete coupling on the edges …
- Raines, Taylor, Takahashi, Timothy T, White, Daniel B, et al.
- Created Date