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