Files in this item

FilesDescriptionFormat

application/pdf

application/pdfLin-AASGNC-18-103.pdf (657kB)
(no description provided)PDF

Description

Title:Attitude control system complexity reduction via tailored viscoelastic damping co-design
Author(s):Lin, Chendi; Herber, Daniel R.; Vedant; Lee, Yong Hoon; Ghosh, Alexander; Ewoldt, Randy H.; Allison, James T.
Subject(s):guidance, navigation, and control
spacecraft
attitude control system
piezoelectric
strain actuator
SASA
viscoelasticity
damping
co-design
Abstract:Intelligent structures utilize distributed actuation, such as piezoelectric strain actuators, to control flexible structure vibration and motion. A new type of intelligent structure has been introduced recently for precision spacecraft attitude control. It utilizes lead zirconate titanate (PZT) piezoelectric actuators bonded to solar arrays (SAs), and bends SAs to use inertial coupling for small-amplitude, high-precision attitude control and active damping. Integrated physical and control system design studies have been performed to investigate performance capabilities and to generate design insights for this new class of attitude control system. Both distributed- and lumped-parameter models have been developed for these design studies. While PZTs can operate at high frequency, relying on active damping alone to manage all vibration requires high-performance control hardware. In this article we investigate the potential value of introducing tailored distributed viscoelastic materials within SAs as a strategy to manage higher-frequency vibration passively, reducing spillover and complementing active control. A case study based on a pseudo-rigid body dynamic model (PRBDM) and linear viscoelasticity is presented. The tradeoffs between control system complexity, passive damping behavior, and overall dynamic performance are quantified.
Issue Date:2018-02-05
Publisher:AAS Rocky Mountain Section
Citation Info:Lin C, Herber DR, Vedant, Lee YH, Ghosh A, Ewoldt RH, and Allison JT. Attitude control system complexity reduction via tailored viscoelastic damping co-design. In AAS Guidance and Control Conference, AAS 18-103, Breckenridge, CO, USA, 2018.
Genre:Conference Paper / Presentation
Type:Text
Image
Language:English
URI:http://hdl.handle.net/2142/106125
Sponsor:This material is based upon work supported by the National Science Foundation under Grant Nos. CMMI-1463203 and CMMI-1653118.
Rights Information:Copyright (c) 2016 by Authors. This paper is released for publication to the American Astronautical Society in all forms.
Date Available in IDEALS:2020-02-24


This item appears in the following Collection(s)

Item Statistics