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Vibration reduction of flexible solar array during orbital maneuver

Vibration reduction of flexible solar array during orbital maneuver Purpose – Orbital maneuver of the spacecraft can cause large‐amplitude vibration of its flexible solar array, which leads to large dynamic stress and a risk of structural failure and fatigue failure. This paper aims to provide a method to reduce such vibration. Design/methodology/approach – Through controlling the rotation at the root of the solar array, a method of vibration reduction is proposed using zero‐placement input shaping technique. Experimental research on a beam scale model of the solar array is performed to verify the effectiveness of the method. Simulation of a detailed example is carried out to investigate whether the method can be applied in engineering. Findings – The experimental results demonstrate the effectiveness of such method. The simulation results indicate that, by adopting the presented method, the vibration induced by orbital maneuver can be diminished remarkably. Research limitations/implications – Studies on the robustness of the method are left for further work. Additionally, since only the first‐order bending vibration of the flexible solar array is eliminated, further improvements are required such that the stated method can be applied to suppress multi‐mode vibration. Practical implications – An effective method is proposed for spacecraft designers planning to actively suppress the vibration of flexible solar array during the process of orbital maneuver. Originality/value – This paper fulfils a source of theoretical and experimental studies for orbital maneuver system design and offers practical help for spacecraft designers. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Vibration reduction of flexible solar array during orbital maneuver

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References (25)

Publisher
Emerald Publishing
Copyright
Copyright © 2014 Emerald Group Publishing Limited. All rights reserved.
ISSN
0002-2667
DOI
10.1108/AEAT-05-2012-0072
Publisher site
See Article on Publisher Site

Abstract

Purpose – Orbital maneuver of the spacecraft can cause large‐amplitude vibration of its flexible solar array, which leads to large dynamic stress and a risk of structural failure and fatigue failure. This paper aims to provide a method to reduce such vibration. Design/methodology/approach – Through controlling the rotation at the root of the solar array, a method of vibration reduction is proposed using zero‐placement input shaping technique. Experimental research on a beam scale model of the solar array is performed to verify the effectiveness of the method. Simulation of a detailed example is carried out to investigate whether the method can be applied in engineering. Findings – The experimental results demonstrate the effectiveness of such method. The simulation results indicate that, by adopting the presented method, the vibration induced by orbital maneuver can be diminished remarkably. Research limitations/implications – Studies on the robustness of the method are left for further work. Additionally, since only the first‐order bending vibration of the flexible solar array is eliminated, further improvements are required such that the stated method can be applied to suppress multi‐mode vibration. Practical implications – An effective method is proposed for spacecraft designers planning to actively suppress the vibration of flexible solar array during the process of orbital maneuver. Originality/value – This paper fulfils a source of theoretical and experimental studies for orbital maneuver system design and offers practical help for spacecraft designers.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Feb 25, 2014

Keywords: Simulation; Experiment; Vibration; Spacecraft; Flexible solar array; Orbital maneuver

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