University of Illinois Urbana-Champaign

Nonlinear attitude control of spacecraft with strain-actuated solar arrays

Nakka, Yashwanth Kumar

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NAKKA-THESIS-2016.pdf

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https://hdl.handle.net/2142/95273

Description

Title
Nonlinear attitude control of spacecraft with strain-actuated solar arrays
Author(s)
Nakka, Yashwanth Kumar
Issue Date
2016-09-02
Director of Research (if dissertation) or Advisor (if thesis)
  • Chung, Soon-Jo
  • Allison, James T.
Department of Study
Aerospace Engineering
Discipline
Aerospace Engineering
Degree Granting Institution
University of Illinois at Urbana-Champaign
Degree Name
M.S.
Degree Level
Thesis
Date of Ingest
2017-03-01T15:45:59Z
Keyword(s)
  • Attitude control
  • Nonlinear control
  • Strain-actuated solar array
  • Lyapunov direct method
  • Piezoelectric material
Abstract
This thesis presents a mathematical framework for precision attitude control of a spacecraft using the inertial coupling between the spacecraft and solar arrays. The spacecraft with solar arrays is modeled as a one degree of freedom cylinder (rigid body rotation) with flexible appendages (infinite-dimensional system). The equations of motion that describe system evolution are derived using the extend generalizations of the Lagrangian for infinite dimension systems. Precision attitude control is achieved by bending the flexible appendage using strain actuators. Global asymptotic convergence of the controller’s is proved using the Lyapunov direct method, which ensures that the control objectives of trajectory tracking and slewing are achieved. The Input-to-State stability of these controllers is used to generalize the control laws in terms of a variable that scales the stiffness term. The closed-loop system is simulated numerically for different values of the variable to verify stability. An experimental setup, that mimics a spacecraft with solar arrays is designed as a cylinder that is secured to a flexible beam using an interference fit. The strain actuation of the beam is achieved using piezoelectric actuators. The rotation of the cylinder and bending in beam are estimated using measurements from a Vicon motion capture system. The closed-loop system is tested in real-time to achieve controlled rotation of the cylinder.
Graduation Semester
2016-12
Type of Resource
text
Permalink
http://hdl.handle.net/2142/95273
Copyright and License Information
Copyright 2016 Yashwanth Kumar Nakka

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Graduate Theses and Dissertations at Illinois
Dissertations and Theses - Aerospace Engineering