PERTURBATIONS OF SATELLITE ORBITS BY THE GRAVITATIONAL ATTRACTION OF A THIRD BODY.

Abstract

Equations giving the rates of change of the six orbital elements of a close satellite due to the gravitational attraction of a third body are derived using Lagrange's planetary equations. Modified expressions are also given for evaluating the perturbations when only first order terms in the eccentricity of the disturbing body are retained. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1965
Accession Number
AD0468941

Entities

People

  • Myrna M. Lewis

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Artificial Satellites
  • Eccentricity
  • Equations
  • Equations Of Motion
  • Mathematics
  • Orbital Elements
  • Orbits
  • Perturbations
  • Satellite Orbits
  • Spacecraft
  • Spacecraft Orbits

Readers

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

Technology Areas

  • Space
  • Space - Orbital Debris