مشروع البحث: EVALUATING SOLAR ARRAY POSITIONING DESIGNS FOR SMALL SATELLITES IN DIFFERENT ORBITS
| dc.contributor.advisor | Advisor: Dr. David. Myszka | |
| dc.date.accessioned | 2026-06-11T10:17:24Z | |
| dc.date.available | 2026-06-11T10:17:24Z | |
| dc.description | generation capabilities of CubeSats pose a major challenge in ensuring the long-term sustainability and reliability of these systems. Evaluating the power generated by solar arrays in a CubeSats satellite is very important and necessary since it has a limitation in the area of the solar arrays, and therefore the energy on board is small. This research will study and evaluate the energy output from a 3U CubeSat in both Geosynchronous and Sun-synchronous orbits with several solar panel design configurations. In addition, this research creates virtual models to determine the weight penalty for advanced positioning devices and ensure the packaged size remains suitable for standard 3U CubeSat. | |
| dc.description.abstract | A CubeSat is a type of miniaturized satellite that is widely used in space research and exploration [12]. They are constructed in cubic, modular units (10cm x 10cm x 10cm) with a mass of 1.3 kg, hence the name “Cubesat”. As shown in Figure 1.1, CubeSats range from 1U to 12U. The concept of CubeSats originated by professors at Stanford University and California Polytechnic State University in 2000. Their aim was for graduate students to gain experience in space research. | |
| dc.identifier | 1329 | |
| dc.identifier.uri | https://dspace.academy.edu.ly/handle/123456789/2286 | |
| dc.subject | EVALUATING SOLAR ARRAY POSITIONING DESIGNS | |
| dc.title | EVALUATING SOLAR ARRAY POSITIONING DESIGNS FOR SMALL SATELLITES IN DIFFERENT ORBITS | |
| dspace.entity.type | Project | |
| project.endDate | 2023 | |
| project.funder.name | هندسة ميكانيكية | |
| project.investigator | محمد علي الصادق محمد | |
| project.startDate | 2022 |