TY - JOUR
T1 - Propellant-free control of tethered formation flight, part 1
T2 - Linear control and experimentation
AU - Chung, Soon Jo
AU - Miller, David W.
N1 - Funding Information:
The authors gratefully acknowledge the NASA Goddard Space Flight Center (Contract Monitor, David Leisawitz) for both financial and technical support for the Massachusetts Institute of Technology Space Systems Laboratory and Payload Systems Synchronized Position Hold, Engage, and Reorient Experimental Satellites Tether program. The authors would like to thank the associate editor (Jesse Leitner) and the anonymous reviewers for their truly constructive feedback. The authors also thank Danielle Adams, Alvar Saenz-Otero, John Merk, Edmund Kong, and Christophe Mandy for the technical discussions and support. The hardware described in this paper has been developed in collaboration with Payload Systems, Inc.
PY - 2008
Y1 - 2008
N2 - We introduce a decentralized attitude control strategy that can dramatically reduce the usage of propellant, by taking full advantage of the physical coupling of the tether. Motivated by a controllability analysis, indicating that both array resizing and spin-up are fully controllable by the reaction wheels and the tether motor, we report the first propellant-free underactuated control results for tethered formation flying spacecraft. This paper also describes the hardware development and experimental validation of the proposed method using the Synchronized Position Hold, Engage, and Reorient Experimental Satellites test bed. In particular, a new relative sensing mechanism that uses six-degree-of-freedom force-torque sensors and rate gyroscopes is introduced and validated in the closed-loop control experiments.
AB - We introduce a decentralized attitude control strategy that can dramatically reduce the usage of propellant, by taking full advantage of the physical coupling of the tether. Motivated by a controllability analysis, indicating that both array resizing and spin-up are fully controllable by the reaction wheels and the tether motor, we report the first propellant-free underactuated control results for tethered formation flying spacecraft. This paper also describes the hardware development and experimental validation of the proposed method using the Synchronized Position Hold, Engage, and Reorient Experimental Satellites test bed. In particular, a new relative sensing mechanism that uses six-degree-of-freedom force-torque sensors and rate gyroscopes is introduced and validated in the closed-loop control experiments.
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U2 - 10.2514/1.32188
DO - 10.2514/1.32188
M3 - Article
AN - SCOPUS:44649150497
SN - 0731-5090
VL - 31
SP - 571
EP - 584
JO - Journal of Guidance, Control, and Dynamics
JF - Journal of Guidance, Control, and Dynamics
IS - 3
ER -