ATTITUDE STABILITY OF ARTICULATED GRAVITY-ORIENTED SATELLITES. PART II - LATERAL MOTION

Abstract

By a procedure similar in principle to that for the longitudinal equations of motion, the lateral equations of a specific compound satellite system were derived. The system is substantially identical with that of the previous report (Part I). As a result of linearization for small perturbations, the effect of orbit ellipticity vanishes in the lateral motion. Both the general case, i.e. with hinged yaw-stabilizers, are discussed. The latter is considered to be better from the practical standpoint. After calculating numerical examples, the configuration was found to provide damping of the lateral motion to 1/2 amplitude in about 0.28 orbits, which is a little better than was previously found for the longitudinal models.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1963
Accession Number
AD0423941

Entities

People

  • H. Maeda

Organizations

  • University of Toronto

Tags

DTIC Thesaurus Topics

  • Aeronautical Engineering
  • Air Force
  • Amplitude
  • Artificial Satellites
  • Coefficients
  • Computer Science
  • Energy
  • Equations
  • Equations Of Motion
  • Euler Angles
  • Government Procurement
  • Inertia
  • Kinetic Energy
  • Mass
  • Moment Of Inertia
  • Perturbations
  • Steepest Descent Method

Readers

  • Control Systems Engineering.
  • Fluid Dynamics.

Technology Areas

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