Optimization of Solar Array Positioning Actuators for Small Satellites

The goal of this research is to evaluate the benefit of actuating solar arrays for small satellites. CubeSats are small satellites that are built to standard dimensions (Units or “U”) of 10 cm x 10 cm x 10 cm. They can be 1U, 2U, 3U, or 6U in size, and weigh less than 1.33 kg (3 lbs) per U. Since their introduction in 1999 by California Polytechnic State University and Stanford University engineers, more than 1100 have been deployed into orbit. CubeSats rely solely on a solar array to generate energy from the sun. The size and weight limitations place constraints on solar panels\u27 size and thus the available power budget and stored energy reserves, which decrease the CubeSat functions. The CubeSats capabilities could be greatly enhanced by increasing the available on-board power. This research determined the energy capturing capability from various solar panel configurations and positioning. Optimal angles of one and two degree-of-freedom positioning. Each configuration of solar cell is simulated for a CubeSats satellite in geo-synchronous and sun-synchronous orbits. In addition, this research will create design models of these various mechanisms configurations by using Sarrus linkage mechanism that elevates the solar cell away from the body of satellite to make sure that these configurations are suitable for the size and weight of the CubeSat.https://ecommons.udayton.edu/stander_posters/2995/thumbnail.jp