Two strategies are presented for semi-autonomous on-board trajectory propagation. One implements a semi-analytic method and rectifies, when needed, a simple on-board (on-line) ephemeris. The method is called rectification in which only several parameters are uplinked to the spacecraft infrequently. The other strategy uses TOPEX/POSEIDON experience to build a data compression device for a wide range of orbits. A trade-off study is conducted to relate accuracy requirements with semi-major axis and eccentricity to minimize the frequency of uplinking.
Semi-Autonomous Spacecraft On-Board Ephemeris Propagation
01.08.1995
Sonstige
Keine Angabe
Englisch
navigation , autonomous , orbit , spacecraft , ephemeris , determination
Semi-Autonomous Spacecraft on-Board Ephemeris Propagation
British Library Conference Proceedings | 1996
|On-Board Ephemeris Determination Using a GPS Receiver for the MSTI-3 Spacecraft
British Library Conference Proceedings | 1997
|AN EXTENDED PROPAGATION EPHEMERIS FOR GNSS
Online Contents | 2006
|AN EXTENDED PROPAGATION EPHEMERIS FOR GNSS
British Library Online Contents | 2006
|