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GPS-Based Navigation and Orbit Determination for the AMSAT Phase 3D SatelliteThis paper summarizes the results of processing GPS data from the AMSAT Phase 3D (AP3) satellite for real-time navigation and post-processed orbit determination experiments. AP3 was launched into a geostationary transfer orbit (GTO) on November 16, 2000 from Kourou, French Guiana, and then was maneuvered into its HEO over the next several months. It carries two Trimble TANS Vector GPS receivers for signal reception at apogee and at perigee. Its spin stabilization mode currently makes it favorable to track GPS satellites from the backside of the constellation while at perigee, and to track GPS satellites from below while at perigee. To date, the experiment has demonstrated that it is feasible to use GPS for navigation and orbit determination in HEO, which will be of great benefit to planned and proposed missions that will utilize such orbits for science observations. It has also shown that there are many important operational considerations to take into account. For example, GPS signals can be tracked above the constellation at altitudes as high as 58000 km, but sufficient amplification of those weak signals is needed. Moreover, GPS receivers can track up to 4 GPS satellites at perigee while moving as fast as 9.8 km/sec, but unless the receiver can maintain lock on the signals long enough, point solutions will be difficult to generate. The spin stabilization of AP3, for example, appears to cause signal levels to fluctuate as other antennas on the satellite block the signals. As a result, its TANS Vectors have been unable to lock on to the GPS signals long enough to down load the broadcast ephemeris and then generate position and velocity solutions. AP3 is currently in its eclipse season, and thus most of the spacecraft subsystems have been powered off. In Spring 2002, they will again be powered up and AP3 will be placed into a three-axis stabilization mode. This will significantly enhance the likelihood that point solutions can be generated, and perhaps more important, that the receiver clock can be synchronized to GPS time. This is extremely important for real-time and post-processed orbit determination, where removal of receiver clock bias from the data time tags is needed, for time-tagging of science observations. Current analysis suggests that the inability to generate point solutions has allowed the TANS Vector clock bias to drift freely, being perhaps as large as 5-7 seconds by October, 2001, thus causing up to 50 km of along-track orbit error. The data collected in May, 2002 while in three-axis stabilized mode should provide a significant improvement in the orbit determination results.
Document ID
20020060774
Acquisition Source
Goddard Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Davis, George
(Emergent Technologies Corp. United States)
Carpenter, Russell
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Moreau, Michael
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Bauer, Frank H.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Long, Anne
(Computer Sciences Corp. United States)
Kelbel, David
(Computer Sciences Corp. United States)
Martin, Thomas
(Van Martin Consulting, Inc. United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2002
Subject Category
Astrodynamics
Meeting Information
Meeting: AIAA GN&C Conference
Location: Monterey, CA
Country: United States
Start Date: August 5, 2002
End Date: August 8, 2002
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NAS5-01090
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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