Continuous, Low Thrust Coplanar Orbit Transfers with Varying Eccentricity

Abstract

The purpose of this study was to investigate the Delta v requirements of a continuous, low thrust spacecraft performing coplanar orbit transfers that are constrained by either constant radius of apogee, perigee, or a combination of the two. The transfers were separated into two timescale problems. The fast timescale involved an optimization of the planar thrust control angle, alpha, to produce the maximum change in eccentricity or semimajor axis over a single revolution. The slow timescale applied the fast timescale results to complete the transfer through many revolutions about the primary body. The constrained radii control laws developed provide optimal circular-to-eccentric and eccentric-to-eccentric orbit transfers. However, when applied to circular-to- circular transfers, the resulting Delta v is nearly twice that obtained using the most optimal continuous thrust control law (alpha = 0), i.e. 'spiral'. Future recommended studies include the development of control laws to provide specified changes in apogee, perigee, and the argument of periapsis. Keywords: Theses, Fortran, Computer program listings.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1988
Accession Number
ADA206022

Entities

People

  • Gregory L. Beeker

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Apogees
  • Artificial Satellites
  • Earth Orbits
  • Eccentric Orbits
  • Electric Propulsion
  • Equations Of Motion
  • Geosynchronous Orbits
  • Ion Propulsion
  • Low Earth Orbits
  • Orbital Elements
  • Orbits
  • Payload
  • Propulsion Systems
  • Spacecraft
  • Thrust
  • Thrust Control
  • Trajectories

Readers

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

Technology Areas

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