Stabilizing an Unstable Orbit about L3 in the Sun, Earth, Moon System Using Linear Constant Gain Feedback.

Abstract

Equations of motion for a satellite in a planar, elliptic four-body system are used to generate an orbit about L3. Initial conditions and a periodic reference orbit were found using a circular four-body model. Linear constant gain feedback is used to stabilize the orbit about L3 in the planar, elliptic four-body model. The computed L3 orbit is plotted against the reference orbit to assess the effectiveness of position, velocity and position/velocity feedback compensation systems. Also computed is the integrated control gain costs for each type of feedback system used. Long term stable motion near libration point L3 was achieved using position/velocity feedback compensation. Position and velocity feedback when used separately were ineffective as stabilizing feedback compensation systems. The integrated control gain costs also indicate that linear constant gain feedback is not an economical method to stabilize this periodic orbit about L3. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1979
Accession Number
ADA079860

Entities

People

  • Doyne E. Smith

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Artificial Satellites
  • Circular Orbits
  • Closed Loop Systems
  • Control Systems
  • Coordinate Systems
  • Differential Equations
  • Engineering
  • Equations
  • Equations Of Motion
  • Feedback
  • Linear Differential Equations
  • Numerical Analysis
  • Orbits
  • Radiation Pressure
  • Solar Wind
  • United States

Readers

  • Control Systems Engineering.
  • Space Exploration and Orbital Mechanics.

Technology Areas

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