Accession Number : ADA188851

Title :   Relative Motion of Two Satellites in Close-Elliptical Orbits.

Descriptive Note : Master's thesis Jan-Dec 87,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s) : Meintel, James M

PDF Url : ADA188851

Report Date : Nov 1987

Pagination or Media Count : 76

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.

Descriptors :   *ELLIPTICAL ORBIT TRAJECTORIES, ACCURACY, ARTIFICIAL SATELLITES, CIRCULAR ORBITS, COMPUTER PROGRAMS, ECCENTRICITY, EQUATIONS OF MOTION, MOTION, ORBITS, RENDEZVOUS TRAJECTORIES, THESES, TRAJECTORIES, HARMONIC ANALYSIS

Subject Categories : Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE