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  • 1
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    Interplanetary orbit determination (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: A general description of the Viking interplanetary orbit determination activity extending from launch to Mars encounter is given. The emphasis is on the technical fundamentals of the problem, basic strategies and data types used, quantitative results, and specific conclusions derived from the inflight experience. Special attention is given to the use of the spacecraft-based optical measurements and their first application as a principal navigational data type for an interplanetary mission. The optical-based orbit determination, in fact, was the primary contributor to the exceptional interplanetary navigation accuracy experienced by both Viking missions. The Viking application of optical orbit determination relied in large part on the technology developed and demonstrated by the Mariner 9 Optical Navigation Demonstration.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Viking Navigation; p 48-108
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The X-windows interactive navigation data editor (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A new computer program called the X-Windows Interactive Data Editor (XIDE) was developed and demonstrated as a prototype application for editing radio metric data in the orbit-determination process. The program runs on a variety of workstations and employs pull-down menus and graphical displays, which allow users to easily inspect and edit radio metric data in the orbit data files received from the Deep Space Network (DSN). The XIDE program is based on the Open Software Foundation OSF/Motif Graphical User Interface (GUI) and has proven to be an efficient tool for editing radio metric data in the navigation operations environment. It was adopted by the Magellan Navigation Team as their primary data-editing tool. Because the software was designed from the beginning to be portable, the prototype was successfully moved to new workstation environments. It was also itegrated into the design of the next-generation software tool for DSN multimission navigation interactive launch support.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: The Telecommunications and Data Acquisition Report; p 66-78
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Mission data system framework description (2002)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: This document provides an overall description of the MDS Framework technology. Since the purpose is to provide a general reference for the frameworks, the descriptions are organized as compendium. This document does not provide guidance for how the MDS technology should be used.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Mission data system architecture and implementation guidelines (2002)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Type: Ground System Architectures Workshop 2002; El Segundo, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    AFS and DFS Growth at JPL (1997)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: The goal for EIS File Service is to develop and deploy a service which encourages all JPL employees and contractors to use DFS to effiently share files, publish web pages, & access tools.
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Statistical analysis of trim maneuvers in low thrust interplanetary navigation (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An analytical technique for the statistical analysis of a low thrust trim maneuver in interplanetary navigation has been developed. The maneuver is treated rigorously as a nonlinear function of the trajectory errors to be removed, and the corresponding nongaussian statistics are developed. The method determines the statistical properties of the maneuver direction and duration, as well as the final state dispersion covariance. The analytical technique is applied to the terminal maneuver in a 1980 Encke slow flyby mission and is found to yield accurate statistical results with much less effort than Monte Carlo simulation. The method permits consideration of a shorter terminal maneuver than does linear analysis, with a consequent improvement in delivery accuracy.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 75-85 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
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  • 7
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    Use of ballistic arcs for low thrust navigation enhancement in the 1980 Encke slow flyby (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A technique is presented for improving navigation accuracy in the Solar Electric Encke Slow Flyby Mission proposed to encounter the comet Encke during its 1980 apparition. The effect of the dominant navigation error source, the high level thruster noise, is reduced through the introduction of a ballistic coast arc for the purpose of orbit determination enhancement. The placement and duration of the arc is investigated with respect to its impact on final delivery error and on control effort required for trajectory correction. Also examined are the changes in delivery accuracy and control effort as a result of the time lag between the state estimation process and the thrust control program update.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-828 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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    NASA TECHNICAL REPORTS
  • 8
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    The determination of the interplanetary orbits of Vikings 1 and 2 (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A description is presented of the navigation-related events of the Viking Mars mission. Orbit determination system fundamentals are discussed, taking into account the trajectory models, observation models, radio data models, range considerations, optical data models, filter models, the orbit determination process, critical orbit determination inputs, and orbit determination errors. Attention is also given to questions of orbit determination strategy, orbit determination results, optical measurements processing, aspects of approach orbit determination evaluation, and the orbit determination software system.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: AIAA PAPER 77-71 , Aerospace Sciences Meeting; Jan 24, 1977 - Jan 26, 1977; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Terminal navigation analysis for the 1980 comet Encke slow flyby mission (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The initial results of a terminal navigation analysis for the proposed 1980 solar electric slow flyby mission to the comet Encke are presented. The navigation technique employs onboard optical measurements with the scientific television camera, groundbased observations of the spacecraft and comet, and groundbased orbit determination and thrust vector update computation. The knowledge and delivery accuracies of the spacecraft are evaluated as a function of the important parameters affecting the terminal navigation. These include optical measurement accuracy, thruster noise level, duration of the planned terminal coast period, comet ephemeris uncertainty, guidance initiation time, guidance update frequency, and optical data rate.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-1063 , Electric Propulsion Conference; Oct 31, 1973 - Nov 02, 1973; Lake Tahoe, NV
    Format: text
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    NASA TECHNICAL REPORTS
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