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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 73 records · Page 4
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NASA NTRS1995

TOPEX/Poseidon Precision Orbit Determination Using Combined GPS, SLR, and DORIS

TOPEX/Poseidon (T/P) is a joint spaceborne oceanographic mission of U.W. NASA and France CNES design launched August 10, 1992. The satellite has a variety tracking systems for both operational and precision orbit determination. Three precise tracking systems: Satellite Laser Ranging (SLR), Doppler Orbitography and Radiopositioning Integrated by Satellite (DORIS), and Global Positioning System (GPS) provide high quality measurements essential for reconstructing the T/P orbital height with centimeter precision. This paper presents results of simultaneously processing all three data types to exploit the inherent strength of each in a combined solution. SLR and DORIS are routinely combined to provide orbit solutions for the T/P science team. GPS orbit solutions are produced as part of the first demonstration flight of a high quality spaceborne GPS receiver. Coordinate frame and software system differences between the combined SLR/DORIS orbits and the GPS orbits induce orbital height differences of 2 to 3 centimeters. Combining the three data types within a single software system permits removal of software system differences while obtaining coordinate frame calibration information. These calibrations will aid future spaceborne GPS missions that are not complemented with SLR and/or DORIS.

TOPEX/Poseidon↗
NASA NTRS1994

Search for Earthquake Effects in TOPEX/Poseidon Data

We have searched TOPEX/Poseidon sea surface height data for effects from six earthquakes of magnitude >6.1 during 1992-1994 in the western Pacific, including the one near Hokkaido, Japan in July 1993.

TOPEX/Poseidon earthquakes tsunamis↗
NASA NTRS1993

TOPEX/POSEIDON Orbit Acquisition Manuever Sequence

TOPEX/POSEIDON....was launched...on August 10, 1992...The Project wanted to achieve operational orbit as soon as possible in order to begin oceanographic data acquisition through altimeters. A sequence of six manuevers was implemented to acquire the operational orbit following injection...

TOPEX TOPEX/POSEIDON manuever sequence design↗
NASA NTRS1993

TOPEX/POSEIDON Orbit Acquisition Manuever Sequence

A sequence of six manuevers was implemented over a 42-day period following the launch of the TOPEX/POSEIDON satellite on August 10, 1992 to acquire an orbit compatible with oceanographic data acquisition requirements as soon as possible...

TOPEX TOPEX/POSEIDON orbit manuevers↗
NASA NTRS1993

Observations of Geographically Correlated Orbit Errors of TOPEX/POSEIDON

We have compared GPS-based dynamic and reduced-dynamic TOPEX/POSEIDON orbits over a 10 day period beginning March 10,1993. The results suggest that the prelaunch gravity model (JGM-1) introduces geographically correlated errors which, when projectd on a mean sea survase, have a storng meridional dependence.

TOPEX/POSEIDON↗
NASA NTRS1993

Automated Precision Orbit Determination for TOPEX/Poseidon with GPS

A highly automated GPS data processing system for the orbit determination of TOPEX/Poseidon is described. The orbit is recovered to an estimated accuracy of better than 4 cm in altitude, 6 cm crosstrack, and 11 cm down track. The RMS postfit residuals on the ionospherically calibrated carrier phase observable are less than 5 mm. The RMS difference over a 4.5-hour overlap period between two 30-hour data arcs is 1 cm in altitude, 5 cm cross track, and 4 cm down track. These results can be obtained within two days of onboard GPS data collection. Most of the data processing for a 30-hour arc of GPS data can be performed on a single workstation in less than 6 hours of CPU time. The estimation scenarios are explained, the automated data processing steps are described, and means to assess solution quality are discussed.

automation GPS data processing orbit determination↗
NASA NTRS1995

Phase Plane Analysis and Observed Frozen Orbit for the TOPEX/Poseidon Mission

The existence and stability of low eccentricity frozen orbits in a zonal geopotential perturbed by atmospheric drag, solar radiation pressure, and a continuous along-track thrust is studied. General expressions are derived for the steady state eccentricity and gravity- only phase plane trajectories. The TOPEX/Poseidon satellite has remained in a frozen orbit throughout its three year primary mission.

TOPEX/Poseidon↗
NASA NTRS1994

On Orbit Measurement of TOPEX/POSEIDON Altimeter Antenna Pattern

The NASA and CNES altimeters on the TOPEX/POSEIDON satellite share a 1.5-meter antenna. Early data suggested that the beam was broader than measured preflight. As corrections which depend on values from the tail of the waveform have been compensated for deviations from the preflight measurements, no appreciable effect on the final data is expected.

TOPEX/POSEIDON↗