Deorbiting Upper-Stages in LEO at EOM using Solar Sails
Journal Title: INCAS BULLETIN - Year 2017, Vol 9, Issue 2
Abstract
This paper analyzes the possibility of deorbiting a launch vehicle upper-stage at end-of-mission from low Earth orbit through the use of a solar sail. Different solar sail sizes are taken into account. The analysis is made via a MATLAB numerical simulation, integrating with the ode45 solver the accelerations arising from geopotential, atmospheric drag and solar radiation pressure. Direct solar pressure and drag augmentation effect are analyzed and a state of the art study in the solar sail research field is performed for a better grasp of the feasibility of the device implementation.
Authors and Affiliations
Alexandru IONEL
Keywords
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- EP ID EP293796
- DOI 10.13111/2066-8201.2017.9.2.9
- Views 78
- Downloads 0
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