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  • 1
    Publication Date: 2005-11-30
    Description: The primary mission is described, which consists of encounters with Venus and Mercury; (a second encounter with Mercury is also possible). The exptected navigation sequences were simulated with a Monte Carlo computer program for the purpose of determining midcourse correction velocity requirements and delivery accuracies. These simulations provide sensitivity in velocity requirements and delivery accuracies to error sources affecting the navigation process. The orbit determination capability at the final pre-Venus maneuver is shown to be the dominant contributor to the velocity requirements for the primary mission. Similarly, the orbit determination capability at the final pre-Mercury maneuver is shown to be the dominant contributor to the delivery accuracy at Mercury.
    Keywords: SPACE SCIENCES
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 104-115
    Format: text
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  • 2
    Publication Date: 2019-07-13
    Description: This paper presents selected navigational aspects of the Mariner Jupiter/Saturn 1977 mission. Emphasis is given to the trajectory correction strategy. In addition to science return and propellant costs, specific considerations affecting the strategy include a large number of candidate trajectories, relatively close satellite flybys, use of trajectory correction maneuvers for trajectory shaping, and the requirement for an optical data type to achieve precision satellite encounters. Finally, important error sources and mission constraints are identified, and their impact on the strategy is discussed.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: AIAA PAPER 75-1098 , American Institute of Aeronautics and Astronautics, Guidance and Control Conference; Aug 20, 1975 - Aug 22, 1975; Boston, MA
    Format: text
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  • 3
    Publication Date: 2019-07-13
    Description: This paper presents the navigational aspects of the Mariner Venus/Mercury 1973 mission. Principal emphasis is on the development of the trajectory correction strategy, propellant costs, and delivery accuracies at Venus and Mercury. Key error sources and mission constraints are discussed. Of particular interest are the statistics of the first, post-Venus, maneuver which must correct for the magnification of errors in the Venus encounter. Finally, although not a primary objective of the mission, the analysis is extended to include a second Mercury encounter.
    Keywords: NAVIGATION
    Type: AAS PAPER 73-243 , Astrodynamics Conference; Jul 16, 1973 - Jul 18, 1973; Vail, CO; US
    Format: text
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