View in EDS

Modeling, robust control synthesis and worst-case analysis for an on-orbit servicing mission with large flexible spacecraft.

Saved in:
Bibliographic Details
Title: Modeling, robust control synthesis and worst-case analysis for an on-orbit servicing mission with large flexible spacecraft.
Authors: Rodrigues, R.1 (AUTHOR) ricardo.rodrigues@isae-supaero.fr, Preda, V.2 (AUTHOR) valentin.preda@esa.int, Sanfedino, F.1 (AUTHOR) francesco.sanfedino@isae-supaero.fr, Alazard, D.1 (AUTHOR) daniel.alazard@isae-supaero.fr
Source: Aerospace Science & Technology. Oct2022, Vol. 129, pN.PAG-N.PAG. 1p.
Subjects: Robust control, Feedback control systems, Dynamic stiffness, Space vehicles, Docks, Kinematic chains, Telecommunication satellites, Artificial satellite attitude control systems
Abstract: This paper outlines a complete methodology for modeling an on-orbit servicing mission scenario and designing a feedback control system for the attitude dynamics that is guaranteed to robustly meet pointing requirements, despite model uncertainties as well as large inertia and flexibility changes throughout the mission scenario. A model of the uncertain plant was derived, which fully captures the dynamics and couplings between all subsystems as well as the decoupled/coupled configurations of the chaser/target system in a single linear fractional representation (LFR). In addition, a new approach is proposed to model and analyze a closed-loop kinematic chain formed by the chaser and the target spacecraft through the chaser's robotic arm, which uses two local spring-damper systems with uncertain damping and stiffness. This approach offers the possibility to model the dynamical behavior of a docking mechanism with dynamic stiffness and damping. The controller was designed by taking into account all the interactions between subsystems and uncertainties as well as the time-varying and coupled flexible dynamics. Lastly, the robust stability and worst-case performances were assessed by means of a structured singular value analysis. The main contribution of this paper is thus to fill an important gap in the literature by obtaining a full analytical LFR model of a rendezvous on-orbit servicing mission including all the different phases of such a scenario, namely the approach phase, capture/docking and manipulation of a target satellite, while taking into account all parametric uncertainties and varying geometrical configurations. [ABSTRACT FROM AUTHOR]
Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
Description
Abstract:This paper outlines a complete methodology for modeling an on-orbit servicing mission scenario and designing a feedback control system for the attitude dynamics that is guaranteed to robustly meet pointing requirements, despite model uncertainties as well as large inertia and flexibility changes throughout the mission scenario. A model of the uncertain plant was derived, which fully captures the dynamics and couplings between all subsystems as well as the decoupled/coupled configurations of the chaser/target system in a single linear fractional representation (LFR). In addition, a new approach is proposed to model and analyze a closed-loop kinematic chain formed by the chaser and the target spacecraft through the chaser's robotic arm, which uses two local spring-damper systems with uncertain damping and stiffness. This approach offers the possibility to model the dynamical behavior of a docking mechanism with dynamic stiffness and damping. The controller was designed by taking into account all the interactions between subsystems and uncertainties as well as the time-varying and coupled flexible dynamics. Lastly, the robust stability and worst-case performances were assessed by means of a structured singular value analysis. The main contribution of this paper is thus to fill an important gap in the literature by obtaining a full analytical LFR model of a rendezvous on-orbit servicing mission including all the different phases of such a scenario, namely the approach phase, capture/docking and manipulation of a target satellite, while taking into account all parametric uncertainties and varying geometrical configurations. [ABSTRACT FROM AUTHOR]
ISSN:12709638
DOI:10.1016/j.ast.2022.107865