Analysis of Practical Employment of Drag Enhanced De-orbiting Devices for Midsized LEO Satellites
Analysis of Practical Employment of Drag Enhanced De-orbiting Devices for Midsized LEO Satellites
The use of drag-enhancing devices for satellite de-orbit has been successfully demonstrated on small satellites, and analysis shows they can be a practical method for de-orbiting many midsized low-earth orbit (LEO) satellites. A satellite's mass, orbital regime, ballistic coefficient, and other characteristics delineate the techniques and trade-offs related to implementing a drag device as a de-orbiting tool. In addition to reviewing the successes of drag devices to date in de-orbited spacecraft, Rhatigan and Lan outlined the trade space available for expansion of this technology to a large range of midsize spacecraft. This study examines that trade space in more detail and with a wide span of existing midsized LEO satellites. Through the analysis of these satellite characteristics and orbital regimes, this study suggests that the potential for fuel mass savings exists for a significant percentage of the midsized satellites. Furthermore, satellites that would still require some propulsion to de-orbit within 25 years show similar fuel mass savings. Drag-enhancing device requirements driven by this study are shown to be achievable within the scope of existing prototypes and realistic drag device designs.
Document information
Analysis of Practical Employment of Drag Enhanced De-orbiting Devices for Midsized LEO Satellites
2021
69 pages
Report
No indication
English
Meteorological Data Collection, Analysis, & Weather Forecasting , Artificial satellites , Case studies , Employment , Low earth orbits , Materials , Meteorological satellites , Propulsion systems , Satellite buses , Small satellites , Solar activity , Solar panels , Solar radiation , Solar sails , Space debris , Space environments , Space systems , Spacecraft
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