Mission Capability Assessment of CubeSats Using a Miniature Ion Thruster
| Title | Mission Capability Assessment of CubeSats Using a Miniature Ion Thruster |
| Publication Type | Journal Article |
| Year of Publication | 2013 |
| Authors | Conversano, Ryan W., and Richard E. Wirz |
| Journal | AIAA Journal of Spacecraft and Rockets |
| Volume | 50 |
| Issue | 5 |
| Pagination | 1035-1046 |
| ISSN | 0022-4650 |
| Keywords | Cubesat, Micropropulsion |
| Abstract | The successful miniaturization of many spacecraft subsystems make CubeSats attractive candidates for evermore demanding scientific missions. A 3U Cubesat employing the Miniature Xenon Ion thruster, which features high efficiency and impulse capability, yields a unique spacecraft that can be optimized for a variety of missions ranging from significant inclination changes in a low Earth orbit to lunar transfers. A nominal configuration of a high-ΔV CubeSat has a dry mass of approximately 6.3 kg, including a 0.75kg payload, margins, and contingencies. Depending on the thruster and propellant tank configuration, this CubeSat is capable of delivering mission ΔV’s from 1000 m/s to over 7000 m/s, enabling low Earth orbit inclination change missions and lunar missions. A parametric analysis on a 3U high-ΔV CubeSat bus revealed that a range of payload volumes (up to nearly 1.4 U) and masses (up to nearly 6 kg) can be accommodated depending on the ΔV requirements and mission type. Additionally, this analysis showed that a high-ΔV 3U CubeSat in a 600 km low Earth orbit can be designed to provide inclination change of over 80°. |
| URL | http://arc.aiaa.org/doi/abs/10.2514/1.A32435 |
| DOI | 10.2514/1.A32435 |
Download File (pdf)
This publication may be downloaded for personal use only. Any other use requires prior permission of the authors and publisher.