University of Illinois Urbana-Champaign

Attitude control system complexity reduction via tailored viscoelastic damping co-design

Lin, Chendi; Herber, Daniel R.; Vedant; Lee, Yong Hoon; Ghosh, Alexander; Ewoldt, Randy H.; Allison, James T.

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https://hdl.handle.net/2142/106125

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.
Issue Date
2018-02-05
Keyword(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.
Publisher
AAS Rocky Mountain Section
Type of Resource
  • text
  • image
Language
en
Permalink
http://hdl.handle.net/2142/106125
Sponsor(s)/Grant Number(s)
This material is based upon work supported by the National Science Foundation under Grant Nos. CMMI-1463203 and CMMI-1653118.
Copyright and License Information
Copyright (c) 2016 by Authors. This paper is released for publication to the American Astronautical Society in all forms.

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