Accession Number : AD0828474

Title :   DIFFERENTIAL EXPRESSIONS RELATING ERRORS IN INITIAL CONDITIONS TO EPHEMERIS ERRORS,

Corporate Author : RCA INTERNATIONAL SERVICE CO PATRICK AFB FL MISSILE TEST SUPPORT

Personal Author(s) : O'Connor, John J.

Report Date : JAN 1968

Pagination or Media Count : 37

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)

Descriptors :   (*ORBITS, MATHEMATICAL ANALYSIS), (*SATELLITE TRACKING SYSTEMS, ACCURACY), GUIDED MISSILE TRAJECTORIES, EPHEMERIDES, POSITION FINDING, PERIGEE, DRAG, GRAVITY, ERRORS, NUMERICAL METHODS AND PROCEDURES.

Subject Categories : Guided Missile Traj, Accuracy and Ballistics
      Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE