Satellite formation reconfiguration and station-keeping using state-dependent Riccati equation technique

Han Earl Park, Sang Young Park, Kyu Hong Choi

Research output: Contribution to journalArticle

31 Citations (Scopus)

Abstract

The current paper presents optimal reconfigurations and formation-keeping for formation flying satellites. The state-dependent Riccati equation (SDRE) technique is utilized as a non-linear controller for both the reconfiguration problem and formation-keeping problem. For the SDRE controller, a state-dependent coefficient (SDC) form is formulated to include non-linearities in the relative dynamics and J2 orbital perturbation. The Taylor series and a transformation matrix are used to establish the SDC form. Optimal reconfiguration trajectories that minimize energy in satellite formation flying are obtained by the SDRE controller and compared with those obtained from a linear quadratic regulator (LQR) and a linear parameter varying (LPV) control method. It is illustrated that the SDRE non-linear controller of the current study obtains relocation accuracy of less than 0.1% of formation base-line length, while the LQR controller and LPV controller yield relatively large relocation errors. The formation-keeping controller developed using the SDRE technique in the current study also provides robustness under severe orbital perturbations.

Original languageEnglish
Pages (from-to)440-452
Number of pages13
JournalAerospace Science and Technology
Volume15
Issue number6
DOIs
Publication statusPublished - 2011 Sep 1

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Riccati equations
Satellites
Controllers
Relocation
Taylor series
Trajectories

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

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abstract = "The current paper presents optimal reconfigurations and formation-keeping for formation flying satellites. The state-dependent Riccati equation (SDRE) technique is utilized as a non-linear controller for both the reconfiguration problem and formation-keeping problem. For the SDRE controller, a state-dependent coefficient (SDC) form is formulated to include non-linearities in the relative dynamics and J2 orbital perturbation. The Taylor series and a transformation matrix are used to establish the SDC form. Optimal reconfiguration trajectories that minimize energy in satellite formation flying are obtained by the SDRE controller and compared with those obtained from a linear quadratic regulator (LQR) and a linear parameter varying (LPV) control method. It is illustrated that the SDRE non-linear controller of the current study obtains relocation accuracy of less than 0.1{\%} of formation base-line length, while the LQR controller and LPV controller yield relatively large relocation errors. The formation-keeping controller developed using the SDRE technique in the current study also provides robustness under severe orbital perturbations.",
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Satellite formation reconfiguration and station-keeping using state-dependent Riccati equation technique. / Park, Han Earl; Park, Sang Young; Choi, Kyu Hong.

In: Aerospace Science and Technology, Vol. 15, No. 6, 01.09.2011, p. 440-452.

Research output: Contribution to journalArticle

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