A Physicist's Guide to J sub 2.

Abstract

This report presents a first-order discussion of the perturbations in the orbital motion of a satellite about an oblate primary. The approach is non-traditional in that the secular changes in the semi-major axis, eccentricity, inclination, and longitude of the ascending node are all derived directly from the translational and rotational equations of motion. The exactly solvable problem of motion in the primary's equatorial plane is used to obtain the advance of the argument of periastron the consequent change in the time of periastron passage. In addition, a simple discussion of a very restricted three-body problem is given to illustrate of the effects of third-body perturbations. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Aug 03, 1979
Accession Number
ADA080492

Entities

People

  • Laurence G. Taff

Organizations

  • Massachusetts Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Angular Momentum
  • Apogees
  • Artificial Satellites
  • Celestial Mechanics
  • Circular Orbits
  • Eccentricity
  • Elliptical Orbits
  • Equations
  • Equations Of Motion
  • Longitude
  • Mechanics
  • Orbital Elements
  • Orbits
  • Perigees
  • Perturbation Theory
  • Perturbations
  • Time Dependence

Fields of Study

  • Physics

Readers

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

Technology Areas

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