Analysis of a CubeSat Orbit Using STK
| dc.contributor.author | Funada, Kenta Patrick | en |
| dc.contributor.committeechair | Black, Jonathan T. | en |
| dc.contributor.committeemember | Lowe, Kevin T. | en |
| dc.contributor.committeemember | Woolsey, Craig A. | en |
| dc.contributor.department | Aerospace and Ocean Engineering | en |
| dc.date.accessioned | 2023-09-06T08:01:00Z | en |
| dc.date.available | 2023-09-06T08:01:00Z | en |
| dc.date.issued | 2023-09-05 | en |
| dc.description.abstract | This thesis presents an analysis of CubeSat orbits for both Low Earth Orbit (LEO) and Sun-Synchronous Orbit (SSO) missions using Systems Tool Kit (STK). The study focuses on analyzing communication, power generation, and radiation exposure while considering various factors. The analysis is based on the 3U CubeSat called UT-ProSat-1, developed by students at Virginia Polytechnic Institute and State University (VT) for an upcoming mission. The orbit size and mass adjustments were made for the LEO mission to enhance communication performance. The influence of solar activity on CubeSat lifetime and access time was examined, highlighting the significance of mass and solar activity. The impact of increasing orbit size on communication time was analyzed, emphasizing the trade-offs between mass, orbit size, and communication performance. The SSO mission prioritized power generation optimization resulted in generating sufficient power for the nominal phase of the mission. It also considered the effects of the South Atlantic Anomaly (SAA) on radiation exposure. Effective risk management of increasing the shielding for the avionics were emphasized which consequently will stabilize the orbit and prolong its lifetime. Additionally, temperature dynamics were investigated, indicating the need for further analysis considering heat dissipation and utilizing a more accurate CubeSat model. The insights gained from this study contribute to the improved the performance of CubeSats and validate the mission results, providing valuable information for successful missions in the future. | en |
| dc.description.abstractgeneral | This project explored the trajectories that small satellites, known as CubeSats, follow around Earth. Two main paths were investigated: the Low Earth Orbit (LEO), which is close to the Earth's surface, and the Sun Synchronized Orbit (SSO), which aligns with the Sun's movement. The software called Systems Tool Kit (STK) served as the simulation tool, helping to analyze the satellites' abilities to communicate, generate power, total space radiation, and satellite's temperature throughout the missions. The study was conducted on the satellite called UT-ProSat-1, a design by students from Virginia Polytechnic Institute and State University (VT). For the LEO path, changes to the satellite's size and weight were applied to analyze its effect on the communication capabilities. Also the Sun's effect on the satellite's operational life and communication windows was assessed. Changes in the satellite's orbit can influence its communication duration, and this necessitates a balance between its weight, trajectory, and communication capacity. Regarding the Sun-aligned path, SSO, the power generated from the Sun was sufficient for the satellite's power needs throughout its mission. A particular space zone with high radiation, the South Atlantic Anomaly (SAA), was evaluated. The majority of total radiation build up on the satellite was determined to came from this area. However, risks associated with this radiation can be minimized by enhancing protection for the satellite's electronics. Such measures not only safeguard the satellite but also increase its stability and longevity in space. The temperature behavior of the satellite was analyzed, underscoring the need for a deeper examination of its thermal patterns. Insights from this study will bolster CubeSat performance and provide valuable information for future successful space missions. | en |
| dc.description.degree | Master of Science | en |
| dc.format.medium | ETD | en |
| dc.identifier.other | vt_gsexam:38337 | en |
| dc.identifier.uri | http://hdl.handle.net/10919/116219 | en |
| dc.language.iso | en | en |
| dc.publisher | Virginia Tech | en |
| dc.rights | In Copyright | en |
| dc.rights.uri | http://rightsstatements.org/vocab/InC/1.0/ | en |
| dc.subject | Vehicle Controls | en |
| dc.subject | Orbital Mechanics | en |
| dc.subject | STK | en |
| dc.title | Analysis of a CubeSat Orbit Using STK | en |
| dc.type | Thesis | en |
| thesis.degree.discipline | Aerospace Engineering | en |
| thesis.degree.grantor | Virginia Polytechnic Institute and State University | en |
| thesis.degree.level | masters | en |
| thesis.degree.name | Master of Science | en |
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