Accession Number : AD0832513
Title : NON-COPLANAR TRANSFER FROM ELLIPTIC AND HYPERBOLIC ORBITS,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Bielkowicz, P.
Report Date : 1966
Pagination or Media Count : 18
Abstract : The following problem is considered in this paper. A vehicle is approaching a planet in a hyperbolic or elliptic planetocentric orbit lying in an arbitrary plane defined by Omega sub 1 and i sub 1. It should be transferred into an elliptic (or hyperbolic) orbit in another given plane defined by Omega sub 2 and i sub 2. The methods presented here show how to find the rectangular equatorial or ecliptic coordinates x, y, z of the transfer point. The obtained solution is given in the form adapted for the substitution of numerical values. Two methods have been analyzed. (Author)
Descriptors : (*TRANSFER TRAJECTORIES, PROBLEM SOLVING), SPACECRAFT, GEOMETRY, ELLIPTICAL ORBIT TRAJECTORIES, NUMERICAL METHODS AND PROCEDURES, TRANSCENDENTAL FUNCTIONS.
Subject Categories : Guided Missile Traj, Accuracy and Ballistics
Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE