Sun-Earth L2 point formation control using polynomial eigenstructure assignment

Feng Wang

doi:10.1016/j.actaastro.2012.02.010

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Sun-Earth L2 point formation control using polynomial eigenstructure assignment

2012-07-01

PRE

DOI：10.1016/j.actaastro.2012.02.010

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Abstract

En 中文

A nonlinear controller based on polynomial eigenstructure assignment (PEA) is presented for the control of Sun-Earth L-2 point formation flying. The relative motion dynamics is formulated as a nonlinear equation and rewritten as a Quasi-Linear Time-Varying (QLTV) model. Using a coprime factorization of the desired closed-loop transfer function, the PEA controller structure is calculated by representing the controller gains as polynomials. During the implementation of spacecraft formation flying, the PEA method is extended from Linear Time-Invariant (LTI) and Linear Parameter-Varying (LPV) models to a QLTV model to produce a closed-loop system with invariant performance over a wide range of conditions. To ensure system performance, the analytic stability analysis of the closed-loop system is developed and a position keeping controller for MIMO formation flying is designed using a decoupling method to achieve the desired performance. Finally, a simulation is carried out to validate the controller performance for the formation flying. (C) 2012 Elsevier Ltd. All rights reserved.

Keywords:

Nonlinear control

Formation flying

Quasi-Linear Time-Varying

Polynomial eigenstructure assignment