|
Server : Apache/2.4.62 System : FreeBSD fbsdweb2.web.rcn.net 14.1-RELEASE FreeBSD 14.1-RELEASE releng/14.1-n267679-10e31f0946d8 GENERIC amd64 User : www ( 80) PHP Version : 8.3.8 Disable Function : NONE Directory : /domains/astrosfm/AAS_meetings/1997_astro/abstracts/ |
Upload File : |
<!DOCTYPE HTML PUBLIC "-//W3C//DTD HTML 3.2//EN">
<HTML>
<HEAD>
<TITLE>Abstract AAS 97-733</TITLE>
</HEAD>
<BODY BGCOLOR="ffffff">
<h2>AAS 97-733</h2>
<h2>THE ANALYSIS OF THE RELATIVE MOTION IN GENERAL ELLIPTIC ORBIT WITH RESPECT TO A DRAGGING AND PRECESSING COORDINATE FRAME </h2>
<h4> J.A. Kechichian - The Aerospace Corporation </h4>
<h2> Abstract </h2>
The full set of second order nonlinear differential equations describing the exact motion of a spacecraft subject to drag and oblateness perturbations in general elliptic orbit, relative to a rotating reference frame which drags and precesses exactly as a given spacecraft attached to its center is derived. This attached spacecraft is itself flying a general elliptic orbit and can be considered as the passive or non-maneuvering vehicle. The unaveraged form of the J2 acceleration is used for both vehicles leaving this oblateness perturbation position dependent for more exacting calculations. These equations can be effectively put to use in calculating by an iterative scheme, the impulsive rendezvous maneuvers in elliptic orbit around the earth or those planets that are either atmosphere bearing or have a dominant second zonal harmonic, or both.