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  • 1
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    Design and development of the ERBE data management system (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Earth radiation budget experiment (ERBE) software development approach is described. An iterative development approach was adopted which provides for three releases or versions of the processing system, each of increasing levels of complexity and solidity. The final release of the system will be used to process the flight data. The major phases for each iterative release consist of specifications developed in concert with the science team, preliminary design, subsystem reviews, coding, subsystem code walkthroughs, system testing, system documentation, and project status review.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 15 p
    Format: text
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  • 2
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    An approximation to midcourse correction direction errors. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A new approximation to the components of midcourse correction direction errors is described that is more accurate than a previously used approximation. The calculation effort involved is much less than that for numerical integration. A comparison of numerical integration results with those of the new approximation is presented in a diagram.
    Keywords: NAVIGATION
    Type: Journal of Spacecraft and Rockets; 9; Sept
    Format: text
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  • 3
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    Round trip Mars missions using looping trajectories in the 1980-2000 time period (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Round trip Mars missions combining a standard trajectory leg and a looping trajectory leg are suggested as an alternative to the more conventional trajectories. Looping trajectories are shown to make it possible to trade a slight increase in total mission time for a significant reduction in Mars stay time, with the possible added benefit of a decrease in energy requirements.
    Keywords: SPACE SCIENCES
    Type: Journal of Spacecraft and Rockets; 10; Oct. 197
    Format: text
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  • 4
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    A multiple-impulse function for orbital transfer and its derivatives (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A multiple-impulse function is represented as a sequence of single-impulse functions. The single-impulse transfer which yields the velocity change required to transfer from a specified initial orbit to a partially specified final orbit is developed. Analytic derivatives of the function are obtained for use in optimization techniques. A four-impulse transfer is outlined. The analytic derivatives may allow more efficient optimization than numerical derivatives do.
    Keywords: SPACE SCIENCES
    Type: NASA-TM-X-2492 , L-8106
    Format: application/pdf
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  • 5
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    Time-fixed rendezvous by impulse factoring with an intermediate timing constraint (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method is presented for factoring a two-impulse orbital transfer into a three- or four-impulse transfer which solves the rendezvous problem and satisfies an intermediate timing constraint. Both the time of rendezvous and the intermediate time of a alinement are formulated as any element of a finite sequence of times. These times are integer multiples of a constant plus an additive constant. The rendezvous condition is an equality constraint, whereas the intermediate alinement is an inequality constraint. The two timing constraints are satisfied by factoring the impulses into collinear parts that vectorially sum to the original impulse and by varying the resultant period differences and the number of revolutions in each orbit. Five different types of solutions arise by considering factoring either or both of the two impulses into two or three parts with a limit for four total impulses. The impulse-factoring technique may be applied to any two-impulse transfer which has distinct orbital periods.
    Keywords: SPACE SCIENCES
    Type: NASA-TR-R-422 , L-9281
    Format: application/pdf
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  • 6
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    A program for contouring randomly spaced data (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description is given of a digital computer program which prepares contour plots of three dimensional data. The contouring technique uses a triangulation procedure. As presently configured, the program can accept up to 56,000 randomly spaced data points, although the required computer resources may be prohibitive. However, with relatively minor internal modifications, the program can handle essentially unlimited amounts of data. Up to 20 contouring intervals can be selected and contoured with either polygonal lines or smooth curves. Sample cases are illustrated. A general description of the main program and primary level subroutines is included to permit simple modifications of the program.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-TM-X-72749
    Format: application/pdf
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  • 7
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    An Earth-Mars mission-analysis program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Rapid, flexible computer program for Earth-Mars trajectory and mission analysis
    Keywords: SPACE SCIENCES
    Type: NASA-TN-D-5985 , L-7213
    Format: application/pdf
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  • 8
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    Modification of an impulse-factoring orbital transfer technique to account for orbit determination and maneuver execution errors (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method has previously been developed to satisfy terminal rendezvous and intermediate timing constraints for planetary missions involving orbital operations. The method uses impulse factoring in which a two-impulse transfer is divided into three or four impulses which add one or two intermediate orbits. The periods of the intermediate orbits and the number of revolutions in each orbit are varied to satisfy timing constraints. Techniques are developed to retarget the orbital transfer in the presence of orbit-determination and maneuver-execution errors. Sample results indicate that the nominal transfer can be retargeted with little change in either the magnitude (Delta V) or location of the individual impulses. Additonally, the total Delta V required for the retargeted transfer is little different from that required for the nominal transfer. A digital computer program developed to implement the techniques is described.
    Keywords: SPACE SCIENCES
    Type: NASA-TM-X-2971 , L-9280
    Format: application/pdf
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  • 9
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    Contouring randomly spaced data (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Computer program using triangulation contouring technique contours data points too numerous to fit into rectangular grid. Using random access procedures, program can handle up to 56,000 data points and provides up to 20 contour intervals for multiple number of parameters.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LAR-12044 , NASA Tech Briefs (ISSN 0145-319X); 1; 3; P. 469
    Format: text
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  • 10
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    Orbital trim by velocity factoring with applications to the Viking mission. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An orbital trim technique has been developed to satisfy terminal rendezvous and intermediate timing constraints for planetary missions involving orbital operations. The technique utilizes a time-open two-impulse transfer from a specified initial orbit to a final orbit which satisfies all geometrical constraints. Each of the two impulses may then be factored, or split, into two or more vectorially equivalent impulses. The periods of the resulting intermediate orbits may be varied along with the number of revolutions in each orbit to satisfy the intermediate and final timing constraints. Factors in the range 0 to 1 result in rendezvous at the same cost as that of the two-impulse transfer. The technique is applied to the Viking mission to Mars although a similar procedure could be utilized for rendezvous operations about any planet.
    Keywords: NAVIGATION
    Type: The growth and maturity of navigation in space; National Space Meeting; Mar 15, 1972 - Mar 16, 1972; Orlando, FL
    Format: text
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