Ionospheric drag for accelerated deorbit from upper low earth orbit

摘要: Abstract Orbit debris mitigation restrictions placed on the growing number of miniaturised spacecraft often constrain their operational altitudes to less than approximately 600km where drag accelerations are sufficient deorbit within 25 year guidelines. Operation at higher, Low Earth (LEO) necessitates active measures such as propulsion systems. However, inclusion systems is not always desirable because added cost and complexity. This work investigates feasibility ionospheric drag, component caused by an electrically charged body’s exchange momentum with ionosphere, accelerate in high LEO (600–1000 km altitude). studies how actively charging surface a satellite may enhance overall magnitude acceleration, due acting spacecraft. achieved using surrogate models coefficient, function plasma scaling parameters, generated Particle-in-Cell simulations. The coefficient model incorporated into orbit propagator times predicted over various orbital vehicular initial conditions. Results suggest that can be order larger neutral 850 altitude compared half 500 altitude. Therefore, relatively more efficient deorbiting drag. Additionally, tailorable based changes electrical potential relative quasi-neutral free-stream plasma. primary payload many require high-voltage These same could conceivably utilised generate via charging, end mission-life, little additional or system Thus, implications this include possible uncovering simple mechanism for from compliance