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  • 1
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    A Comparison of Trajectory Optimization Methods for the Impulsive Minimum Fuel Rendezvous Problem (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: In this paper we present a comparison of optimization approaches to the minimum fuel rendezvous problem. Both indirect and direct methods are compared for a variety of test cases. The indirect approach is based on primer vector theory. The direct approaches are implemented numerically and include Sequential Quadratic Programming (SQP), Quasi-Newton, Simplex, Genetic Algorithms, and Simulated Annealing. Each method is applied to a variety of test cases including, circular to circular coplanar orbits, LEO to GEO, and orbit phasing in highly elliptic orbits. We also compare different constrained optimization routines on complex orbit rendezvous problems with complicated, highly nonlinear constraints.
    Keywords: Spacecraft Propulsion and Power
    Type: 26th Annual Guidance and Control Conference; Feb 01, 2003 - Feb 28, 2003; Breckenridge, CO; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The General Mission Analysis Tool (GMAT): Current Features And Adding Custom Functionality (2010)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The General Mission Analysis Tool (GMAT) is a software system for trajectory optimization, mission analysis, trajectory estimation, and prediction developed by NASA, the Air Force Research Lab, and private industry. GMAT's design and implementation are based on four basic principles: open source visibility for both the source code and design documentation; platform independence; modular design; and user extensibility. The system, released under the NASA Open Source Agreement, runs on Windows, Mac and Linux. User extensions, loaded at run time, have been built for optimization, trajectory visualization, force model extension, and estimation, by parties outside of GMAT's development group. The system has been used to optimize maneuvers for the Lunar Crater Observation and Sensing Satellite (LCROSS) and ARTEMIS missions and is being used for formation design and analysis for the Magnetospheric Multiscale Mission (MMS).
    Keywords: Computer Programming and Software; Astrodynamics
    Type: LEGNEW-OLDGSFC-GSFC-LN-1107 , International Conference on Astrodynamics Tools and Techniques (ICATT); May 03, 2010 - May 06, 2010; Madrid; Spain
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A Comparison of Trajectory Optimization Methods for the Impulsive Minimum Fuel Rendezvous Problem (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In this paper we present, a comparison of trajectory optimization approaches for the minimum fuel rendezvous problem. Both indirect and direct methods are compared for a variety of test cases. The indirect approach is based on primer vector theory. The direct approaches are implemented numerically and include Sequential Quadratic Programming (SQP). Quasi- Newton and Nelder-Meade Simplex. Several cost function parameterizations are considered for the direct approach. We choose one direct approach that appears to be the most flexible. Both the direct and indirect methods are applied to a variety of test cases which are chosen to demonstrate the performance of each method in different flight regimes. The first test case is a simple circular-to-circular coplanar rendezvous. The second test case is an elliptic-to-elliptic line of apsides rotation. The final test case is an orbit phasing maneuver sequence in a highly elliptic orbit. For each test case we present a comparison of the performance of all methods we consider in this paper.
    Keywords: Spacecraft Propulsion and Power
    Type: 26th Annual Guidance and Control Conference; Feb 01, 2003 - Feb 28, 2003; Breckenridge, CO.; United States
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
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