Speaker
Mr
EVIATAR EDLERMAN
(Technion)
Description
Nanosatellite clusters constitute one of the current and future trends in space technology. [1] These clusters can be used in a variety of applications including search and rescue, communication, earth monitoring, etc. In order to maintain a satellite cluster over a long period of time it is required that the inter-satellite distances between the cluster agents will be controlled. [2] The nanosatellites need to mitigate the along-track drift created by the initial orbit injection, using the very limited resources available onboard. In the mass range of 1 – 10 kg, Cubesats have strict constraints on allowed mass, volume, electrical power, and carry only limited sensor and actuator capability. [3]
This paper explores the capability of state of the art miniaturized electric propulsion (EP) systems to establish and maintain a nanosatellite cluster mission. Different EP technologies will be considered. Due to the low thrust provided by an EP system, long orbit control maneuvers are required. Therefore, mission design is highly effected by long-term attitude and power constraints. In contrast to previous work that either ignored the attitude limitations or assumed that the satellite orientation is dedicated to the orbit control maneuver, [4] the proposed paper will focus on developing an autonomous controller that can work under realistic attitude and mission constraints.
The paper compares 6 types of satellite body forms, with deployable and body fixed solar panels, each with its own constraints on mass, volume, and power. The paper will present the results of the analysis and provide a conclusion regarding the possibility of current EP technology to be applied for maintaining a nanosatellite cluster.
[1] Alfriend, K. T., Vadali, S. R., Gurfil, P., How, J. P., and Breger, L. S., Spacecraft Formation Flying: Dynamics, Control and Navigation, Elsevier Astrodynamics, New York, 2010.
[2] Kronhaus, I., Schilling, K., Pietzka, M., and Schein, J. “Simple Orbit and Attitude Control using Vacuum Arc Thrusters for Picosatellites,” Journal of Spacecraft and Rockets, American Institute of Aeronautics and Astronautics, Vol. 51, No. 6, 2014, pp. 2008-2015.
[3] CubeSat Design Specification Rev. 13 The CubeSat Program, Cal Poly SLO
[4] Ruggiero, A., Pergola, P., Marcuccio, S., and Andrenucci, M., “Low-Thrust Maneuvers for the
Efficient Correction of Orbital Elements,” 32nd International Electric Propulsion Conference, September 9-11, Wiesbaden, Germnay, 2011. IEPC-2011-102."
| Applicant type | First author |
|---|
Primary author
Mr
EVIATAR EDLERMAN
(Technion)
Co-author
Mr
Kronhaus Igal
(Technion - Israel Institute of Technology)
