microGPS: On-orbit Demonstration of a New Approach to GPS to Space Applications
In February 1998 Student Nitric Oxide Explorer (SNOE) was successfully launched and began scientific observations.
Student↗
Engineering topics
Bertiger, W.
Publications and source records attributed to Bertiger, W..
Precise Real-Time Low Earth Orbitor Navigation With GPS
Technology is currently available to support real-time on-board knowledge of the position of a low earth orbitor at the 5-15 meter level using the civilian broadcast GPS signal with sophisticated models and filtering techniques onboard the spacecraft.
Navigation Low Earth Orbitor GPS↗
Assessment of GPS Occultations for Atmospheric Profiling
the concept of utilizing the global positioning system signals as a means of sensing the atmosphere has been studied in some detail in the literature.
global positioning system atmospheric profiling↗
Ephemeris and Clock Navigation Message Accuracy
We discuss the accuracy of the ephemeris and clock corrections contained in the GPS navigation message.
satellite parameters↗
Processing DORIS Data with the GIPSY/OASIS II Software for Precise Positioning and Orbit Determination: First Results and Intercomparisons
Explore the source record for details and available documents.
TOPEX TOPEX/POSEIDON GIPSY/OASIS II SPOT2↗
First Assessment of GPS-Based Reduced Dynamic Orbit Determination of TOPEX/Poseidon
The reduced dynamic tracking technique has been applied for the first time as part of the GPS experiment on TOPEX/Poseidon.
TOPEX/Poseidon↗
High precision GPS orbit determination using March 1985 demonstration data
Preliminary orbit determination for satellites in the U.S. Department of Defense's Global Positioning System has been performed using GPS carrier phase data collected in March-April 1985 at 10 sites in the continental United States. The data were analyzed using a new data processing software package called GIPSY (GPS Inferred Positioning SYstem) and with existing covariance analysis software. Data from one day have been processed with average formal position errors of 1.4 to 3.6 meters. The true errors are probably somewhat larger. Covariance results are presented which suggest that the orbits can be obtained with formal errors under 2 meters after certain software issues are resolved.
Bertiger, W.↗