Modeling of Inflation Rates and Mechanical Creation of Reflective Sphere to Harness Solar Radiation Pressure for Medium Earth Orbit Satellites

Abstract

This study proposes a dynamic model for the trajectory of a non-functional satellite with an inflatable spherical solar sail that acts as a de-orbiting device by harnessing Solar Radiation Pressure (SRP) and varying area-to-mass ratios. The model mimics real-world behaviors by using equations of motion that feature natural perturbations and SRP calculations using the cannonball model and shadow function. The time needed for the proposed balloon to push medium Earth orbit space debris back into the atmosphere is calculated for various binary and linear inflation methods. The results indicate that for satellites in near-circular orbits with an initial semi-major axis of 22,000 km, the solar sail can be deployed to push them into atmospheric re-entry within about 34.96 or 50.14 years for initial orbital inclinations of 0.001 or 56.06 degrees, respectively. For a GPS satellite with a semi-major axis of 26,560 km and inclination of 55 degrees, de-orbiting occurs within 61.3602 years. There is a potential for the improvement of these times by using a larger balloon or more reflective material. Alternative materials and compressor specifications are explored, though future advancements in these technologies are required to prove the feasibility of a mechanical model.