Finite-time control for spacecraft body-fixed hovering over an asteroid

Daero Lee; Amit Sanyal; Eric Butcher; Daniel Scheeres

doi:10.1109/TAES.2014.140197

Finite-time control for spacecraft body-fixed hovering over an asteroid

Daero Lee, Amit Sanyal, Eric Butcher, Daniel Scheeres

Research output: Contribution to journal › Article › peer-review

84 Scopus citations

Abstract

A finite-time control scheme for autonomous body-fixed hovering of a rigid spacecraft over a tumbling asteroid is presented. The relative configuration between the spacecraft and asteroid is described in terms of exponential coordinates on the Lie group SE(3), which is the configuration space for the spacecraft. With a Lyapunov stability analysis, the finite-time convergence of the proposed control scheme for the closed-loop system is proved. Numerical simulations validate the performance of the proposed control scheme.

Original language	English (US)
Article number	7073509
Pages (from-to)	506-520
Number of pages	15
Journal	IEEE Transactions on Aerospace and Electronic Systems
Volume	51
Issue number	1
DOIs	https://doi.org/10.1109/TAES.2014.140197
State	Published - Jan 1 2015
Externally published	Yes

ASJC Scopus subject areas

Aerospace Engineering
Electrical and Electronic Engineering

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10.1109/TAES.2014.140197

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abstract = "A finite-time control scheme for autonomous body-fixed hovering of a rigid spacecraft over a tumbling asteroid is presented. The relative configuration between the spacecraft and asteroid is described in terms of exponential coordinates on the Lie group SE(3), which is the configuration space for the spacecraft. With a Lyapunov stability analysis, the finite-time convergence of the proposed control scheme for the closed-loop system is proved. Numerical simulations validate the performance of the proposed control scheme.",

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AU - Butcher, Eric

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AB - A finite-time control scheme for autonomous body-fixed hovering of a rigid spacecraft over a tumbling asteroid is presented. The relative configuration between the spacecraft and asteroid is described in terms of exponential coordinates on the Lie group SE(3), which is the configuration space for the spacecraft. With a Lyapunov stability analysis, the finite-time convergence of the proposed control scheme for the closed-loop system is proved. Numerical simulations validate the performance of the proposed control scheme.

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Finite-time control for spacecraft body-fixed hovering over an asteroid

Abstract

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