Akademik Veri Yönetim Sistemi
AAS/AIAA Astrodynamics Specialist Conference, 2020, Virtual, Online, 9 - 12 Ağustos 2020, cilt.175, ss.2387-2406
Exploiting the propellant free maneuver capability of solar sail satellites for high resolution Earth observation mission is addressed with an elliptical low Earth orbit. The employed orbit has a low perigee altitude for observation and a high apogee altitude for orbit maneuvers. For the purpose of mission analysis of this new concept, a reference satellite configuration is designed with an aim to determine the technological readiness level based on the characteristic acceleration. Finally, a mission orbit parameter selection algorithm for a region of interest is developed based on observation performance metrics. The new concept is shown to be successful in carrying out propellant-free Earth observation.