Citation
Abstract
An approximation to the topocentric range rate of a spacecraft is developed which is first order in both the time past epoch and the ratio between the distance of an observing station from the geocenter and the geocentric range. This approximation is compared with a numerical integrated trajectory to obtain some idea of the duration over which it may be reliable. The development is extended to include an analytical determination of the errors in the spacecraft state produced by errors in the range rate data. It is also shown how range data may be incorporated into this cursory error analysis. The partial derivatives of the gravitatienal geocentric acceleration with respect to range, declination, and right ascension are obtained analytically and shown graphically.
Details
- Volume
- III
- Published
- June 15, 1971
- Pages
- 77–93
- File Size
- 1.4 MB