DIFFERENTIAL EXPRESSIONS RELATING ERRORS IN INITIAL CONDITIONS TO EPHEMERIS ERRORS,
Abstract
Equations are derived for expressing ephemeris errors in terms of errors in the classical orbital elements, drag parameter and gravitational constant at epoch. Ephemeris errors are described in the radial, in-track and cross track coordinate system. The equations are simple enough for hand computation, have been validated by numerical integration with a sophisticated orbit generator and have been found useful in trajectory analysis at the Air Force Eastern Test Range. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1968
- Accession Number
- AD0828474
Entities
People
- John J. O'connor