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  • 1
    Publication Date: 2005-11-27
    Description: Ray tracing techniques for examination of refractivity profile sensitivity in tropospheric range and Doppler effects on profile shape
    Keywords: GEOPHYSICS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 22-30
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  • 2
    Publication Date: 2005-11-30
    Description: Earth-based radio tracking data types are considered, which involve simultaneous or nearly simultaneous spacecraft tracking from widely separated tracking stations. These data types are conventional tracking instrumentation analogs of the very long baseline interferometry (VLBI) of radio astronomy-hence the name quasi-VLBI. A preliminary analysis of quasi-VLBI is presented using simplified tracking data models. The results of accuracy analyses are presented for a representative mission, Viking 1975. The results indicate that, contingent on projected tracking system accuracy, quasi-VLBI can be expected to significantly improve navigation performance over that expected from conventional tracking data types.
    Keywords: NAVIGATION
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 116-132
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  • 3
    Publication Date: 2005-11-30
    Description: A simple point of view is presented for establishing the relationship between a general modeling error and estimation accuracy. Tentative models are given for the random, nongravitational forces thought likely to affect the Mariner 6 and 7 spacecraft. The navigation data from these spacecraft were used to determine the relativity parameter Gamma. The effect that random accelerations have on the classical least squares filter, which assumes the accelerations do not exist, is calculated, and it is demonstrated that their presence seriously affects the estimates, particularly when an extended data arc is employed. Finally, some preliminary exploration using sequential-type filters, which attempt to model and thus ameliorate the effects of these same accelerations, is reported.
    Keywords: MATHEMATICS
    Type: Proc. of the Conf. on Exptl. Tests of Gravitation Theories; p 148-157
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  • 4
    Publication Date: 2011-08-16
    Description: Station longitude error effects on Doppler plus range and Doppler only orbit determination solutions, emphasizing Viking mission trajectory
    Keywords: NAVIGATION
    Type: The Deep Space Network, Vol. 4; p 71-77
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  • 5
    Publication Date: 2011-08-16
    Description: Six parameter model of range-rate observable showing differenced tracking data for improved orbit determination with constant accelerations
    Keywords: COMMUNICATIONS
    Type: The Deep Space Network, Vol. 4; p 61-70
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  • 6
    Publication Date: 2011-08-16
    Description: Three parameter model of differenced tracking data types applied to zero declination and process noise problems for improved orbit determination
    Keywords: COMMUNICATIONS
    Type: The Deep Space Network, Vol. 4; p 49-60
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  • 7
    Publication Date: 2011-08-17
    Description: When two interplanetary spacecraft lie along similar geocentric lines-of-sight, navigational advantages may be achieved by navigating one spacecraft with respect to the other. Opportunities to employ this technique will become more common as more multiprobe missions are launched. The two Viking spacecraft and the two Mariner Jupiter/Saturn '77 spacecraft will be within two and three degrees of each other, respectively, for a large portion of their missions. Results of simulated analysis as well as the processing of real tracking data from the two Viking spacecraft reveal the following advantages of the dual spacecraft navigation technique: (1) cancellation of platform parameter and transmission media modeling errors in short arc solutions, (2) accurate encounter guidance for the trailing spacecraft, (3) reduction of total tracking requirements, and (4) rapid determination of the orbit following a maneuver on either spacecraft.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: The Deep Space Network; p 55-65
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  • 8
    Publication Date: 2011-08-17
    Description: Simultaneous one way Doppler demonstrations performed on Pioneer 11 are described. The data noise of the differenced one way doppler as computed from the pseudo residuals is around 0.002 Hz, which is nearly an order of magnitude smaller than the one way Doppler noise and about the same as differenced two way/three way Doppler noise. The demonstration results and the applicability of differenced one way radio metric data to spacecraft navigation are discussed.
    Keywords: COMMUNICATIONS AND RADAR
    Type: The Deep Space Network; p 104-110
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  • 9
    Publication Date: 2017-10-02
    Description: Time synchronization between two sites using differential GPS has been investigated by a number of researchers. When the two sites are widely separated, the common view period of any GPS satellite becomes shorter; low elevation observations are inevitable. This increase the corrupting effects of the atmospheric delay and, at the same time, narrows the window for such time synchronization. This difficulty can be alleviated by synchronization. This difficulty can be alleviated by using a transit site located midway between the two main sites. The main sites can now look at different GPS satellites which are also in view at the transit site. However, a ground transit site may not always be conveniently available, especially across the Pacific Ocean; also, the inclusion of a ground transit site introduce additional errors due to its location error and local atmospheric delay. An alternative is to use a low Earth orbiter (LEO) as the transit site. A LEO is superior to a ground transit site in three ways: (1) It covers a large part of the Earth in a short period of time and, hence, a single LEO provides worldwide transit services; (2) it is above the troposphere and thus its inclusion does not introduce additional tropospheric delay error; and (3) it provides strong dynamics needed to improve GPS satellite positions which are of importance to ultraprecise time synchronization.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NRL Proc. of the 15th Ann. Precise Time and Time Interval (PTTI) Appl. and Planning Meeting; p 371-388
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  • 10
    Publication Date: 2019-07-27
    Description: Various components of outer planet navigation systems are examined using the Saturn portion of a MJS77 Mission as an example. Special emphasis is placed upon the planet relative and satellite relative orbit determination performance. The effects of constant and stochastic error sources are investigated by means of covariance studies, simulations, and worst case analyses. Preliminary requirements for both the quality of the radiometric and optical data, and for the a priori knowledge of satellite and planetary ephemerides are given for various levels of navigational accuracy. Mission benefits resulting from improved navigational capabilities are discussed.
    Keywords: NAVIGATION
    Type: AIAA PAPER 72-926 , American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, Palo Alto; Sept. 11-12, 1972; Palo Alto, CA
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