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A Novel Dynamic Model of a Reaction Wheel Assembly for High Accuracy Pointing Space Missions

[+] Author Affiliations
Francesco Sanfedino, Daniel Alazard, Valérie Pommier-Budinger

DCAS ISAE-SUPAERO, Toulouse, France

Fabrice Boquet

ESA/ESTEC, Noordwjik, Netherlands

Alexandre Falcoz

Airbus D&S, Toulouse, France

Paper No. DSCC2018-8918, pp. V003T40A002; 10 pages
doi:10.1115/DSCC2018-8918
From:
  • ASME 2018 Dynamic Systems and Control Conference
  • Volume 3: Modeling and Validation; Multi-Agent and Networked Systems; Path Planning and Motion Control; Tracking Control Systems; Unmanned Aerial Vehicles (UAVs) and Application; Unmanned Ground and Aerial Vehicles; Vibration in Mechanical Systems; Vibrations and Control of Systems; Vibrations: Modeling, Analysis, and Control
  • Atlanta, Georgia, USA, September 30–October 3, 2018
  • Conference Sponsors: Dynamic Systems and Control Division
  • ISBN: 978-0-7918-5191-3
  • Copyright © 2018 by ASME

abstract

This paper proposes a novel dynamic model of a Reaction Wheel Assembly (RWA) based on the Two-Input Two-Output Port framework, already presented by the authors. This method allows the user to study a complex system with a sub-structured approach: each sub-element transfers its dynamic content to the other sub-elements through local attachment points with any set of boundary conditions. An RWA is modelled with this approach and it is then used to study the impact of typical reaction wheel perturbations on a flexible satellite in order to analyze the micro-vibration content for a high accuracy pointing mission. This formulation reveals the impact of any structural design parameter and highlights the need of passive isolators to reduce the micro-vibration issues. The frequency analysis of the transfer between the disturbance sources and the line-of-sight (LOS) jitter highlights the role of the reaction wheel speed on the flexible modes migration and suggests which control strategies can be considered to mitigate the residual micro-vibration content in order to fulfil the mission performances.

Copyright © 2018 by ASME

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