The Cluster Orbits With Perturbations of Keplerian Elements (COWPOKE) Equations

Abstract

Recent developments have indicated that it is possible to express the relative equations of motion for space objects in non-circular orbits using mean Keplerian elements and low order expansions. This report provides the initial derivation of one such effort known as the Cluster Orbits With Perturbations Of Keplerian Elements (COWPOKE) equations. Given mean Keplerian elements and element differences, the COWPOKE equations describe spherical radial, cross-track, and along-track separations of the satellites as an explicit function of time. The framework of the equations allows for very high eccentricity reference orbits and for the inclusion of dynamic perturbations. Test cases using two-body dynamics show the utility of this approach.

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Document Details

Document Type
Technical Report
Publication Date
Mar 20, 2004
Accession Number
ADA424880

Entities

People

  • Chris Sabol
  • Craig Mclaughlin
  • Kim Luu

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Apogees
  • Artificial Satellites
  • Circular Orbits
  • Coordinate Systems
  • Dynamics
  • Earth Orbits
  • Eccentric Orbits
  • Equations
  • Equations Of Motion
  • Low Earth Orbits
  • Orbital Elements
  • Orbits
  • Relative Motion
  • Space Objects
  • Spacecraft

Readers

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

Technology Areas

  • Space
  • Space - Orbital Debris