Relative Motion of Two Satellites in Close-Elliptical Orbits.

Abstract

The need for a closed form solution for two bodies in close elliptical orbits is identified. Equations of motion are derived using Hamilton's equations. Floquet theory, and its applicability to this problem, is discussed. The solution for circular orbits is derived in closed form and numerically, using Floquet theory and harmonic analysis. To confirm the accuracy of the computer code. Next the solution for elliptical - orbits is found numerically first for very small eccentricities, finding the dependence on eccentricity. The solution is then found for all time as a function of eccentricity. Keywords: Orbit trajectories; Artificial satellite orbits; Rendezvous trajectories.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1987
Accession Number
ADA188851

Entities

People

  • James M. Meintel

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Artificial Satellites
  • Celestial Mechanics
  • Circular Orbits
  • Computational Science
  • Coordinate Systems
  • Differential Equations
  • Eccentricity
  • Eigenvalues
  • Elliptical Orbits
  • Engineering
  • Equations
  • Equations Of Motion
  • Harmonic Analysis
  • Orbits
  • Relative Motion
  • Trajectories

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Control Systems Engineering.

Technology Areas

  • Space
  • Space - Orbital Debris