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  • 1
    Publication Date: 2019-06-27
    Description: Information pertinent to users of the program to optimize simulated trajectories (POST) is presented. The input required and output available is described for each of the trajectory and targeting/optimization options. A sample input listing and resulting output are given.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-132690 , MCR-75-143-VOL-2
    Format: application/pdf
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  • 2
    Publication Date: 2019-06-27
    Description: Information pertinent to the programmer and relating to the program to optimize simulated trajectories (POST) is presented. Topics discussed include: program structure and logic, subroutine listings and flow charts, and internal FORTRAN symbols. The POST core requirements are summarized along with program macrologic.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-132691 , MCR-75-143-VOL-3
    Format: application/pdf
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  • 3
    Publication Date: 2019-06-27
    Description: A general purpose FORTRAN program for simulating and optimizing point mass trajectories (POST) of aerospace vehicles is described. The equations and the numerical techniques used in the program are documented. Topics discussed include: coordinate systems, planet model, trajectory simulation, auxiliary calculations, and targeting and optimization.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-132689 , MCR-75-143-VOL-1
    Format: application/pdf
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  • 4
    Publication Date: 2019-06-27
    Description: A decomposition algorithm is presented which optimizes complex missions by partitioning the trajectory into natural segments such as ascent or entry. Each segment defines a full-rank targeting subproblem. These are solved sequentially using the Newton-Raphson algorithm. The master problem, representing the complete mission, is to determine subproblem targets and master-problem controls that optimize the mission objective subject to intersegment constraints. The gradient projection algorithm solves this problem using derivatives obtained analytically from finite-difference subproblem sensitivities. Thus, the mission is optimized by coordinating the solution of tractible subproblems. Computational results for a synchronous equatorial mission are included.
    Keywords: ASTRODYNAMICS
    Type: Journal of Spacecraft and Rockets; 14; Nov. 197
    Format: text
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  • 5
    Publication Date: 2019-07-13
    Description: POST/6D POST is set of two computer programs providing ability to target and optimize trajectories of powered or unpowered spacecraft or aircraft operating at or near rotating planet. POST treats point-mass, three-degree-of-freedom case. 6D POST treats more-general rigid-body, six-degree-of-freedom (with point masses) case. Used to solve variety of performance, guidance, and flight-control problems for atmospheric and orbital vehicles. Applications include computation of performance or capability of vehicle in ascent, or orbit, and during entry into atmosphere, simulation and analysis of guidance and flight-control systems, dispersion-type analyses and analyses of loads, general-purpose six-degree-of-freedom simulation of controlled and uncontrolled vehicles, and validation of performance in six degrees of freedom. Written in FORTRAN 77 and C language. Two machine versions available: one for SUN-series computers running SunOS(TM) (LAR-14871) and one for Silicon Graphics IRIS computers running IRIX(TM) operating system (LAR-14869).
    Keywords: MECHANICS
    Type: LAR-14869 , LAR-14871 , NASA Tech Briefs (ISSN 0145-319X); 18; 2; P. 60
    Format: text
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  • 6
    Publication Date: 2019-07-13
    Description: A decomposition algorithm is presented that optimizes complex missions by partitioning the trajectory into natural segments such as ascent or entry. Each segment defines a full-rank targeting subproblem. These are solved sequentially using the Newton-Raphson algorithm. The master problem, representing the complete mission, is to determine subproblem targets and master-problem controls that optimize the mission objective subject to intersegment constraints. The gradient projection algorithm solves this problem using derivatives obtained analytically from finite-difference subproblem sensitivities. Thus, the mission is optimized by coordinating the solution of tractible subproblems. Computational results for a synchronous equatorial mission are included.
    Keywords: ASTRODYNAMICS
    Type: AAS PAPER 75-054 , Astrodynamics Specialist Conference; Jul 28, 1975 - Jul 30, 1975; Nassau; Bahamas
    Format: text
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