Optimal Attitude Control of an Orbiting Satellite Containing Flexible Appendages.

Abstract

This thesis investigated three methods for obtaining optimal control requirements for satellites having flexible appendages. A discrete method, modal method, and a new integral coordinate method for obtaining control requirements were examined. Mathematical formulation was performed on a satellite configuration consisting of a symmetrical rigid body with two flexible antennas extending in opposite directions along the spin axis. System equations of motion were derived using Hamilton's equations. Modern optimal control theory, involving the minimization of a quadratic cost functional and the numerical solution to the steady state matrix Riccati equation, was applied to the system. The results of this thesis indicate that the integral coordinate technique provides a valid and useful means of obtaining realistic estimates of control requirements for the class of satellites under consideration.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1977
Accession Number
ADA048369

Entities

People

  • Vincent Thomas Cilmi

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Angular Motion
  • Artificial Satellites
  • Circular Orbits
  • Closed Loop Systems
  • Computer Programs
  • Differential Equations
  • Eigenvalues
  • Equations Of Motion
  • Modal Analysis
  • Moment Of Inertia
  • Resonant Frequency
  • Riccati Equation
  • Satellite Orientation
  • Space Systems
  • Spacecraft
  • Vehicles

Fields of Study

  • Engineering

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Robotics and Automation.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Satellites
  • Space - Spacecraft Maneuvers