Abstract The possibility of maintaining a group of pico-satellites in a bounded formation, using very low power electric propulsion, is presented. A model predictive controller is used to develop a simple control scheme that avoids the need for on-line orbit determination. The control law, verified using a high fidelity propagator, is capable of maintaining a group of pico-satellites within a 1500 km region at an average ΔV of 2.5 m/s per month. In order to reduce the power requirements of the attitude and propulsion systems, a combined control is utilized. Attitude accuracy is shown to be better than 0.5 deg. The combined attitude-orbit control and the simplicity of the control law provide important advantage for implementation in a pico-satellite with extremely limited resources.
[1]
Klaus Schilling,et al.
Communication in Distributed Satellite Systems
,
2013
.
[2]
W. H. Clohessy,et al.
Terminal Guidance System for Satellite Rendezvous
,
2012
.
[3]
Clifford A. Sedlund.
A simple sun-pointing magnetic controller for satellites in equatorial orbits
,
2009,
2009 IEEE Aerospace conference.
[4]
Daniel E. Hastings,et al.
Distinguishing Attributes for the Operationally Responsive Space Paradigm
,
2008
.
[5]
Eduardo F. Camacho,et al.
Robust Model Predictive Control for Spacecraft Rendezvous with Online Prediction of Disturbance Bounds
,
2009
.