DESIGN OF A LOW EARTH ORBIT ORIGAMI SATELLITE PROTOTYPE

Abstract

Current day structures such as satellites, while relatively flexible, have limitations when it comes to combining aerodynamic stabilization and deployability. While a small number of studies have investigated the idea of utilizing air molecule density for aerodynamic stabilization in Low Earth Orbits, no reliable solutions for proper deployment were given. Here we report our findings in regards to investigating the feasibility of creating a Low Earth Orbit satellite that incorporates folding and unfolding mechanisms based on origami design. The designing process included creation of a 3D model assembly and associated technical drawings in SolidWorks, kinematic synthesis and mathematical modeling in GeoGebra software, as well as the creation of the final physical prototype with an Arduino-based control system. A PID controller was designed and tuned to control magnetic torque of the satellite, with the three satellite configurations simulated: symmetric deployed, symmetric folded, and asymmetric deployed. The altitude motion of the three shapes were tested for performance in 200, 400, 600, and 800 km altitudes using code in MATLAB software. The simulation results have shown that asymmetrical shape change leads to a shift in aerodynamic characteristics of the satellite, with smaller control input interference compared to symmetric shapes. Overall, the project has demonstrated the possibility of merging aerodynamics with the design principles of origami, and has provided possible advantages of employing such a satellite in the real world. However, further study is needed in the future for investigation of costs and practicality of using an origami-based satellite in space research.