Mohamed Ali Alsadig Mohamed
Download Project (595 KB)
CubeSats are standard and modularized satellites that have gained widespread implementation among the scientific research community due to their low cost of manufacture and launch. The only source of energy for CubeSat missions are from solar arrays, which are coupled to rechargeable batteries that provide power during the shaded portion of the orbit. The goal of this research is to maximize the energy per weight ratio of solar array designs for a 3U CubeSat. The solar array configurations investigated include rigidly mounted to the CubeSat sides, and deployed with zero, one, and two degree of freedom, active positioning actuation schemes. Numerical models are created for multiple variations of geo-synchronous and sun-synchronous orbits, which are common for CubeSat missions. The results for orbit parameters and energy acquisition for rigid-mounted solar arrays are validated with commercially available orbital mechanics software (SDK). The various solar cell designs are evaluated based on their energy acquisition potential and actuation complexity and weight of design.
Dave Harry Myszka
Primary Advisor's Department
Mechanical and Aerospace Engineering
Stander Symposium Posters, School of Engineering
United Nations Sustainable Development Goals
Affordable and Clean Energy
"Optimization of Solar Array Positioning Actuators for Small Satellites" (2021). Stander Symposium Projects. 2378.