Analysis of Practical Employment of Drag Enhanced De-orbiting Devices for Midsized LEO Satellites
Abstract
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 Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2021
- Accession Number
- AD1150953
Entities
People
- Adam J. Fuller
Organizations
- Naval Postgraduate School