Deorbiting Upper-Stages in LEO at EOM using Solar Sails
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 acce...
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| Format: | Article |
| Language: | English |
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National Institute for Aerospace Research “Elie Carafoli” - INCAS
2017-06-01
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| Series: | INCAS Bulletin |
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| Online Access: | http://bulletin.incas.ro/files/ionel_a__vol_9_iss_2.pdf |
| Summary: | 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. |
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| ISSN: | 2066-8201 2247-4528 |