OPTIMUM FEEDBACK CONTROL OF A SYNODIC SATELLITE.

Abstract

A control system is devised to minimize the fuel required to maintain a satellite at the three-body libration point between the earth and moon bodies in the planar very restricted four-body model. The problem is formulated as a linear regulator problem of variational calculus for equations of motion linearized about the libration point. The solution yields a linear feedback control system that is optimal with respect to a quadratic performance criterion. A matrix Riccati equation is solved to obtain the feedback gains. The control system is extended to include the nonlinear system dynamics with the steady-state feedback gains of the linear problem. The performance of the resulting control system is analyzed on a digital computer. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0695043

Entities

People

  • Walter D. Seward

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Artificial Satellites
  • Computers
  • Control Systems
  • Differential Equations
  • Digital Computers
  • Equations
  • Equations Of Motion
  • Feedback
  • Nonlinear Systems
  • Regulators
  • Riccati Equation
  • Steady State

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Robotics and Automation.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Orbital Debris
  • Space - Spacecraft Maneuvers