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  • 1
    Publication Date: 2011-08-24
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: Journal of the Astronautical Sciences (ISSN 0021-9142); 40; 3; p. 369-406.
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  • 2
    Publication Date: 2011-08-19
    Description: The determination of improved orbits for the Neptunian satellites Triton and Nereid is discussed. The primary results are the final set of model parameters which generate orbits that best fit both the earth-based satellite observations and data acquired by the Voyager spacecraft during the Neptune encounter. The accuracy of the improved orbits is assessed and they are compared with the orbits generated prior to the encounter. Mean elements are also provided as a geometrical representation for the orbits.
    Keywords: ASTRONOMY
    Type: Astronomy and Astrophysics (ISSN 0004-6361); 247; 2, Ju
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  • 3
    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 2992, Accession no. A82-38893
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 301-306
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  • 4
    Publication Date: 2018-06-08
    Description: This paper discusses orbit determination results for the Galileo satellite tour. Lacking a high gain antenna, the mission will use a low gain antenna for communication and tracking. This change implies far less navigation data will be available than previously expected. A baseline orbit analysis was completed assuming this decreased data schedule. Variations on this baseline were studied to determine sensitivity to data loss. Results indicate that the probability of completing the tour is less than 90 percent, although future improvements in orbit determination promise to raise the probability of completion above 90 percent.
    Keywords: Astrodynamics
    Type: AAS/AIAA: Astrodynamics Conference; Victoria, British Columbia; Canada
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  • 5
    Publication Date: 2018-06-08
    Description: The first fully autonomous deep-space navigation system ever implemented is planned to guide the New Millenium Deep Space-1 mission to an asteroid and comet beginning in mid-1998. This system is based to a large extent on Optical Navigation (OPNAV) technology developed for the NASA/JPL interplanetary exploration probes Voyager and Galileo. This paper describes the structure and algorithmic content of the Autonomous OPNAV system. The system has several major autonomous functions: picture planning, image analysis, orbit determination, manuever design and general interaction with other onboard autonomous systems.
    Keywords: Lunar and Planetary Science and Exploration
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  • 6
    Publication Date: 2019-06-28
    Description: Optical observations were necessary during the Voyager II Uranus approach and encounter in order to meet mission navigational requirements. In this paper, the overall optical navigation system and operation at Uranus are outlined. The formulation of the optical observables are presented, as well as their subsequent integration into the overall orbit determination products. Optical data analysis and some resulting orbit determination results from Uranus are shown. Certain scientifically important results were natural outcomes of the optical data analysis, and these are also reviewed. Finally, certain optical navigation related problems are anticipated at the forthcoming Neptune encounter in 1989; these are briefly discussed as are plans to deal with them.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: AIAA PAPER 86-2113
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  • 7
    Publication Date: 2019-06-28
    Description: The Voyager II flyby of Uranus in January 1986 was the most distant planetary encounter ever attempted, and presented unique challenges to the process of orbit determination. Long light-times and spacecraft receiver difficulties hampered the collection of two-way radiometric data and helped bring about the maturation of a Very Long Baseline Interferometry navigational data type during the long cruise from Saturn. Planet and satellite ephemeris uncertainties necessitated the use of the onboard spacecraft optical system for Uranus-relative navigation. During the close approach phase, these optical data were combined with radiometric data to drive the Uranus system-relative uncertainties down to the level of a few tens of kilometers. This paper contains qualitative and quantitative results and conclusions based on orbit determination experience during Uranus cruise and encounter. Topics include an overview of the navigation-related mission events and requirements, and a review of the salient orbit determination results.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 86-2112
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  • 8
    Publication Date: 2019-06-28
    Description: The use of synthetic aperture radar (SAR) images to estimate orbital parameters is studied. The SAR image formation process which requires the ability to repeatedly transmit identical signals and accurately sense the return echoes from a region of terrain is described. The orbit determination capabilities of the SAR system's observables are investigated. Five SAR observations were collected from a simulated shuttle orbit, which was circular with a latitude of 220 km and along-track velocity of 7.7 km/sec, to obtain along-track and line-of-sight direction position measurements; the simulation reveals that only three SAR observations were required to determine the position of the spacecraft to within 100 m. A prototype SAR orbit determination system was developed. The system consists of a VAX 11/780 time-shared computer, a frame buffer, topographic maps, and software for line-pixel location of an object within a SAR image and for orbit determination. The prototype is applied to the processing of a single short arc of Shuttle Imaging-Radar-B (SIR-B) data. It is observed that the SAR data is useful as orbit determination or tracking data; however, the low SNRs in the SIR-B data made feature identification difficult.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: AAS PAPER 85-412
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  • 9
    Publication Date: 2019-06-28
    Description: Uranian satellite ephemerides were needed by the Voyager project to support both navigation and acquisition of scientific data. This paper outlines the mathematical modeling approach taken to generate those ephemerides and discusses their pre-encounter development, real time updating, and post-encounter refinement. The results presented include the final set of model parameters which generate the ephemerides that best fit the Voyager optical data as well as the earth based observations of the satellites.
    Keywords: ASTRONOMY
    Type: AIAA PAPER 86-2059
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  • 10
    Publication Date: 2016-06-07
    Description: Voyager radio navigation made use of a differenced rage data type for both Saturn encounters because of the low declination singularity of Doppler data. Nearly simultaneous two-way range from two-station baselines was explicitly differenced to produce this data type. Concurrently, a differential VLBI data type (DDOR), utilizing doubly differenced quasar-spacecraft delays, with potentially higher precision was demonstrated. Performance of these data types is investigated on the Jupiter-to-Saturn leg of Voyager 2. The statistics of performance are presented in terms of actual data noise comparisons and sample orbit estimates. Use of DDOR as a primary data type for navigation to Uranus is discussed.
    Keywords: COMMUNICATIONS AND RADAR
    Type: The Telecommun. and Data Acquisition Progr. J.; p 40-52
    Format: application/pdf
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