NON-COPLANAR TRANSFER FROM ELLIPTIC AND HYPERBOLIC ORBITS,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1966
- Accession Number
- AD0832513
Entities
People
- P. Bielkowicz
Organizations
- Air Force Institute of Technology